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1. 发明授权

US08651805B2 Hot gas path component cooling system 有权
标题翻译：热气路组件冷却系统
公开(公告)号：US08651805B2
公开(公告)日：2014-02-18
申请号：US12765372
申请日：2010-04-22
申请人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
发明人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F01D25/14
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译：公开了一种用于热气路径部件的冷却系统。冷却系统可以包括组件层和覆盖层。组件层可以包括第一内表面和第二外表面。第二外表面可以限定多个通道。组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。多个通道中的每一个可以流体地连接到多个通道中的至少一个。覆盖层可以位于邻近部件层的第二外表面处。多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。多个通道可以被配置成流过冷却介质，冷却覆盖层。

2. 发明申请

US20110259017A1 HOT GAS PATH COMPONENT COOLING SYSTEM 有权
标题翻译：热气路成分冷却系统
公开(公告)号：US20110259017A1
公开(公告)日：2011-10-27
申请号：US12765372
申请日：2010-04-22
申请人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
发明人： Benjamin Paul Lacy , Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F02C7/12 , F28F13/18
CPC分类号： F01D25/12 , F01D5/186 , F01D5/187 , F02C7/12 , F05D2230/11 , F05D2230/13 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2260/201 , F05D2260/202 , F05D2260/22141
摘要： A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.
摘要翻译：公开了一种用于热气路径部件的冷却系统。冷却系统可以包括组件层和覆盖层。组件层可以包括第一内表面和第二外表面。第二外表面可以限定多个通道。组件层可以进一步限定大体上在第一内表面和第二外表面之间延伸的多个通道。多个通道中的每一个可以流体地连接到多个通道中的至少一个。覆盖层可以位于邻近部件层的第二外表面处。多个通道可以被配置成将冷却介质流动到多个通道并且向覆盖层提供冲击冷却。多个通道可以被配置成流过冷却介质，冷却覆盖层。

3. 发明授权

US08376706B2 Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method 有权
标题翻译：涡轮翼型凹形冷却通道采用双旋流动机构及方法
公开(公告)号：US08376706B2
公开(公告)日：2013-02-19
申请号：US11863744
申请日：2007-09-28
申请人： Ronald Scott Bunker , Gary Michael Itzel
发明人： Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译：涡轮机翼片包括具有凹形冷却流道的前缘。凹形冷却流道的顶点将流动通道分成相邻的区域。涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。

4. 发明申请

US20090087312A1 Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method 有权
标题翻译：涡轮机翼冷却通道采用双旋流动机理和方法
公开(公告)号：US20090087312A1
公开(公告)日：2009-04-02
申请号：US11863744
申请日：2007-09-28
申请人： Ronald Scott Bunker , Gary Michael Itzel
发明人： Ronald Scott Bunker , Gary Michael Itzel
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/314 , F05D2250/33 , F05D2250/70 , F05D2260/205 , F05D2260/2212 , F05D2260/22141 , F05D2260/2322
摘要： A turbine airfoil includes a leading edge having a concave cooling flow passage. An apex of the concave cooling flow passage divides the flow passage into adjacent regions. The turbine airfoil includes a first plurality of turbulators disposed in one of the adjacent regions, and a second plurality of turbulators disposed in the other of the adjacent regions. The first and second pluralities of turbulators are positioned relative to one another to divert cooling flow in opposing swirl streams that recombine along the apex and to effect a desired heat transfer and pressure loss.
摘要翻译：涡轮机翼片包括具有凹形冷却流道的前缘。凹形冷却流道的顶点将流动通道分成相邻的区域。涡轮机翼片包括设置在相邻区域之一中的第一多个湍流器和设置在相邻区域中的另一个中的第二多个湍流器。第一和第二多个紊流器相对于彼此定位，以使沿着顶点重新组合的相反旋流中的冷却流转向并实现所需的传热和压力损失。

5. 发明授权

US08857055B2 Process and system for forming shaped air holes 有权
标题翻译：用于形成成形气孔的工艺和系统
公开(公告)号：US08857055B2
公开(公告)日：2014-10-14
申请号：US12697005
申请日：2010-01-29
申请人： Bin Wei , Jon Conrad Schaeffer , Ronald Scott Bunker , Wenwu Zhang , Kathleen Blanche Morey , Jane Marie Lipkin , Benjamin Paul Lacy , Wilbur Douglas Scheidt
发明人： Bin Wei , Jon Conrad Schaeffer , Ronald Scott Bunker , Wenwu Zhang , Kathleen Blanche Morey , Jane Marie Lipkin , Benjamin Paul Lacy , Wilbur Douglas Scheidt
IPC分类号： B21D53/78 , B21K3/04 , B23P15/02 , F02C7/18 , F01D25/12 , B23K26/38 , B23K26/06 , B23K26/30 , B23K26/08
CPC分类号： F02C7/18 , B23K26/0624 , B23K26/082 , B23K26/384 , B23K26/389 , B23K26/60 , B23K26/702 , B23K2101/001 , B23K2101/34 , F01D25/12 , F05D2230/00 , F05D2230/13 , Y10T29/49316 , Y10T29/4932 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49348 , Y10T29/49799
摘要： A process is provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
摘要翻译：提供了一种用于形成成形气孔的方法，例如用于涡轮叶片。本公开的方面涉及使用短脉冲激光器形成空气孔的成形部分，形成与每个成形部分相对应的计量孔，并且使用短脉冲激光单独精加工成形部分。在其他实施例中，可以改变这些操作的顺序，诸如形成成形部分，并且在形成相应的计量孔之前使用短脉冲激光来完成成形部分。

6. 发明授权

US08905713B2 Articles which include chevron film cooling holes, and related processes 有权
标题翻译：包括人字形薄膜冷却孔的文章及相关工艺
公开(公告)号：US08905713B2
公开(公告)日：2014-12-09
申请号：US12790675
申请日：2010-05-28
申请人： Ronald Scott Bunker , Benjamin Paul Lacy
发明人： Ronald Scott Bunker , Benjamin Paul Lacy
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2230/10 , Y02T50/67 , Y02T50/672 , Y02T50/676 , Y10T29/49316
摘要： An article is described, including an inner surface which can be exposed to a first fluid; an inlet; and an outer surface spaced from the inner surface, which can be exposed to a hotter second fluid. The article further includes at least one row or other pattern of passage holes. Each passage hole includes an inlet bore extending through the substrate from the inlet at the inner surface to a passage hole-exit proximate to the outer surface, with the inlet bore terminating in a chevron outlet adjacent the hole-exit. The chevron outlet includes a pair of wing troughs having a common surface region between them. The common surface region includes a valley which is adjacent the hole-exit; and a plateau adjacent the valley. The article can be an airfoil. Related methods for preparing the passage holes are also described.
摘要翻译：描述了一种制品，包括可暴露于第一流体的内表面; 一个入口以及与内表面间隔开的外表面，其可以暴露于较热的第二流体。该制品还包括至少一行或其它图案的通道孔。每个通孔包括从内表面的入口延伸穿过基底的入口孔，靠近外表面的通道孔出口，入口孔终止于邻近孔出口的人字形出口。人字形出口包括一对翼槽，它们之间具有共同的表面区域。公共表面区域包括与孔出口相邻的谷部; 和毗邻山谷的高原。文章可以是一个翼型。还描述了制备通道孔的相关方法。

7. 发明申请

US20110185572A1 PROCESS AND SYSTEM FOR FORMING SHAPED AIR HOLES 有权
标题翻译：用于形成形状的空气的过程和系统
公开(公告)号：US20110185572A1
公开(公告)日：2011-08-04
申请号：US12697005
申请日：2010-01-29
申请人： Bin Wei , Jon Conrad Schaeffer , Ronald Scott Bunker , Wenwu Zhang , Kathleen Blanche Morey , Jane Marie Lipkin , Benjamin Paul Lacy , Wilbur Douglas Scheidt
发明人： Bin Wei , Jon Conrad Schaeffer , Ronald Scott Bunker , Wenwu Zhang , Kathleen Blanche Morey , Jane Marie Lipkin , Benjamin Paul Lacy , Wilbur Douglas Scheidt
IPC分类号： B21D53/00 , B23P17/00 , B23K26/00
CPC分类号： F02C7/18 , B23K26/0624 , B23K26/082 , B23K26/384 , B23K26/389 , B23K26/60 , B23K26/702 , B23K2101/001 , B23K2101/34 , F01D25/12 , F05D2230/00 , F05D2230/13 , Y10T29/49316 , Y10T29/4932 , Y10T29/49336 , Y10T29/49339 , Y10T29/49341 , Y10T29/49348 , Y10T29/49799
摘要： A process and system are provided for forming shaped air holes, such as for use in turbine blades. Aspects of the disclosure relate to forming shaped portions of air holes using a short pulse laser, forming a metered hole corresponding to each shaped portion, and separately finishing the shaped portion using a short-pulse laser. In other embodiments, the order of these operations may be varied, such as to form the shaped portions and to finish the shaped portions using the short-pulse laser prior to forming the corresponding metered holes.
摘要翻译：提供了用于形成诸如用于涡轮叶片的成形气孔的过程和系统。本公开的方面涉及使用短脉冲激光器形成空气孔的成形部分，形成与每个成形部分相对应的计量孔，并且使用短脉冲激光单独精加工成形部分。在其他实施例中，可以改变这些操作的顺序，诸如形成成形部分，并且在形成相应的计量孔之前使用短脉冲激光来完成成形部分。

8. 发明申请

US20110293423A1 ARTICLES WHICH INCLUDE CHEVRON FILM COOLING HOLES, AND RELATED PROCESSES 有权
标题翻译：其中包括CHEVRON膜冷却孔及相关工艺
公开(公告)号：US20110293423A1
公开(公告)日：2011-12-01
申请号：US12790675
申请日：2010-05-28
申请人： Ronald Scott Bunker , Benjamin Paul Lacy
发明人： Ronald Scott Bunker , Benjamin Paul Lacy
IPC分类号： F01D5/18 , B21D53/78
CPC分类号： F01D5/186 , F05D2230/10 , Y02T50/67 , Y02T50/672 , Y02T50/676 , Y10T29/49316
摘要： An article is described, including an inner surface which can be exposed to a first fluid; an inlet; and an outer surface spaced from the inner surface, which can be exposed to a hotter second fluid. The article further includes at least one row or other pattern of passage holes. Each passage hole includes an inlet bore extending through the substrate from the inlet at the inner surface to a passage hole-exit proximate to the outer surface, with the inlet bore terminating in a chevron outlet adjacent the hole-exit. The chevron outlet includes a pair of wing troughs having a common surface region between them. The common surface region includes a valley which is adjacent the hole-exit; and a plateau adjacent the valley. The article can be an airfoil. Related methods for preparing the passage holes are also described.
摘要翻译：描述了一种制品，包括可暴露于第一流体的内表面; 一个入口以及与内表面间隔开的外表面，其可以暴露于较热的第二流体。该制品还包括至少一行或其它图案的通道孔。每个通孔包括从内表面的入口延伸穿过基底的入口孔，靠近外表面的通道孔出口，入口孔终止于邻近孔出口的人字形出口。人字形出口包括一对翼槽，它们之间具有共同的表面区域。公共表面区域包括与孔出口相邻的谷部; 和毗邻山谷的高原。文章可以是一个翼型。还描述了制备通道孔的相关方法。

9. 发明授权

US09284231B2 Hydrocarbon film protected refractory carbide components and use 有权
$Hydrocarbon film protected refractory carbide components and use$
标题翻译：碳膜保护耐火硬质合金元件和使用
公开(公告)号：US09284231B2
公开(公告)日：2016-03-15
申请号：US13328704
申请日：2011-12-16
申请人： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
发明人： William Paul Minnear , Ronald Scott Bunker , Narendra Digamber Joshi , Andrei Tristan Evulet
IPC分类号： F02C7/08 , C04B41/80 , C04B41/00 , F01D25/12 , F02C7/12
CPC分类号： F02C7/16 , C04B41/0072 , C04B41/009 , C04B41/80 , F01D15/10 , F01D25/12 , F02C7/12 , F05D2260/232 , Y02T50/672 , Y02T50/676 , C04B35/56 , C04B35/565 , C04B35/806 , C04B41/4529
摘要： A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
摘要翻译：公开了一种具有由高碳活性气体由烃提供的难熔碳化物的稳定化的涡轮发电系统。本公开还包括使用高碳活性气体来稳定热气路径成分的方法。

10. 发明授权

US08727727B2 Components with cooling channels and methods of manufacture 有权
标题翻译：具有冷却通道和制造方法的部件
公开(公告)号：US08727727B2
公开(公告)日：2014-05-20
申请号：US12965083
申请日：2010-12-10
申请人： Ronald Scott Bunker , Todd Garrett Wetzel
发明人： Ronald Scott Bunker , Todd Garrett Wetzel
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/147 , F01D5/28 , F01D5/288 , F05D2260/202 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A component is disclosed. The component includes a substrate comprising an outer surface and an inner surface. The inner surface defines at least one hollow, interior space, and the outer surface defines one or more grooves that extend at least partially along the outer substrate surface and have a respective base. One or more access holes are formed through the base of a respective groove, to connect the groove in fluid communication with the respective hollow interior space. The component further includes a coating comprising one or more layers disposed over at least a portion of the outer substrate surface. The groove(s) and the coating together define one or more channels for cooling the component. One or more trenches are formed through one or more coating layers and at least partially define at least one exit region for the cooling channel(s). A method of fabricating a component is also provided.
摘要翻译：公开了一个组件。该组件包括包括外表面和内表面的基底。内表面限定至少一个中空的内部空间，并且外表面限定一个或多个凹槽，其至少部分地沿着外部衬底表面延伸并且具有相应的底座。通过相应凹槽的基部形成一个或多个通孔，以将凹槽与相应的中空内部空间流体连通。该组件还包括涂层，其包括设置在外基材表面的至少一部分上的一层或多层。凹槽和涂层一起限定一个或多个通道以冷却部件。一个或多个沟槽通过一个或多个涂层形成，并且至少部分地限定用于冷却通道的至少一个出口区域。还提供了一种制造部件的方法。

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