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71. 发明申请

US20120036858A1 COMBUSTOR LINER COOLING SYSTEM 有权
标题翻译： COMBUSTOR内胆冷却系统
公开(公告)号：US20120036858A1
公开(公告)日：2012-02-16
申请号：US12855156
申请日：2010-08-12
申请人： Benjamin Paul Lacy , Mert Enis Berkman
发明人： Benjamin Paul Lacy , Mert Enis Berkman
IPC分类号： F02G3/00
CPC分类号： F23R3/002 , F23R3/005
摘要： A combustor liner is disclosed. The combustor liner includes an upstream portion, a downstream end portion extending from the upstream portion along a generally longitudinal axis, and a cover layer associated with an inner surface of the downstream end portion. The downstream end portion includes the inner surface and an outer surface, the inner surface defining a plurality of microchannels. The downstream end portion further defines a plurality of passages extending between the inner surface and the outer surface. The plurality of microchannels are fluidly connected to the plurality of passages, and are configured to flow a cooling medium therethrough, cooling the combustor liner.
摘要翻译：公开了一种燃烧器衬套。燃烧器衬套包括上游部分，沿着大致纵向轴线从上游部分延伸的下游端部分以及与下游端部分的内表面相关联的覆盖层。下游端部包括内表面和外表面，内表面限定多个微通道。下游端部还限定在内表面和外表面之间延伸的多个通道。多个微通道流体地连接到多个通道，并且构造成使冷却介质流过其中，冷却燃烧器衬套。

72. 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。

73. 发明授权

US09303517B2 Channel marker and related methods 有权
标题翻译：频道标记和相关方法
公开(公告)号：US09303517B2
公开(公告)日：2016-04-05
申请号：US13524055
申请日：2012-06-15
申请人： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , David Edward Schick , Brian Lee Tollison
发明人： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , David Edward Schick , Brian Lee Tollison
IPC分类号： F01D5/18 , C23C14/04 , F01D5/28
CPC分类号： F01D5/288 , B23H1/00 , B23K1/0018 , B23K31/02 , C23C4/01 , C23C14/042 , F01D5/186 , F05D2230/30 , F05D2230/90 , F05D2260/204
摘要： Various embodiments of the disclosure include a component, methods of forming components, and methods of cooling components. In some embodiments, a component is disclosed including: a body; a microchannel extending through a portion of the body; a thermal barrier coating (TBC) covering a portion of the microchannel; and a marker member extending from the microchannel through the TBC or from an end of the microchannel, the marker member indicating a location of the microchannel in the body.
摘要翻译：本公开的各种实施例包括部件，形成部件的方法和冷却部件的方法。在一些实施例中，公开了一种组件，包括：主体; 延伸穿过身体的一部分的微通道; 覆盖微通道的一部分的热障涂层（TBC）; 以及从微通道穿过TBC或从微通道的端部延伸的标记构件，标记构件指示微通道在体内的位置。

74. 发明授权

US09273561B2 Cooling structures for turbine rotor blade tips 有权
标题翻译：涡轮转子叶片尖端的冷却结构
公开(公告)号：US09273561B2
公开(公告)日：2016-03-01
申请号：US13566202
申请日：2012-08-03
申请人： Benjamin Paul Lacy , Randall Richard Good , Brian Gene Brzek
发明人： Benjamin Paul Lacy , Randall Richard Good , Brian Gene Brzek
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/20 , F01D5/186 , F05D2250/182
摘要： A rotor blade for a turbine of a combustion turbine engine having an airfoil that includes a pressure and a suction sidewall defining an outer periphery and a tip portion defining an outer radial end. The tip portion includes a rail that defines a tip cavity. The airfoil includes an interior cooling passage configured to circulate coolant. The rotor blade further includes: a slotted portion of the rail; and at least one film cooling outlet disposed within at least one of the pressure sidewall and the suction sidewall of the airfoil. The film cooling outlet includes a position that is adjacent to the tip portion and in proximity to the slotted portion of the rail.
摘要翻译：一种用于燃气涡轮发动机的涡轮机的转子叶片，其具有包括压力的翼型和限定外周的吸力侧壁和限定外径向端的尖端部分。尖端部分包括限定尖端腔的轨道。翼型件包括构造成使冷却剂循环的内部冷却通道。转子叶片还包括：轨道的开槽部分; 以及设置在翼型件的压力侧壁和吸力侧壁中的至少一个内的至少一个薄膜冷却出口。薄膜冷却出口包括邻近尖端部分并且靠近导轨的开槽部分的位置。

75. 发明授权

US09127549B2 Turbine shroud cooling assembly for a gas turbine system 有权
标题翻译：用于燃气轮机系统的涡轮机罩冷却组件
公开(公告)号：US09127549B2
公开(公告)日：2015-09-08
申请号：US13456407
申请日：2012-04-26
申请人： Benjamin Paul Lacy , David Edward Schick , David Wayne Weber
发明人： Benjamin Paul Lacy , David Edward Schick , David Wayne Weber
IPC分类号： F01D11/08 , F01D5/00 , F01D5/08 , F01D25/14 , F01D25/26 , F01D5/22 , F01D25/12
CPC分类号： F01D5/00 , F01D5/08 , F01D5/084 , F01D5/225 , F01D25/12 , F01D25/14 , F01D25/26 , F05D2260/201 , F05D2260/204
摘要： A turbine shroud cooling assembly for a gas turbine system includes an outer shroud component disposed within a turbine section of the gas turbine system and proximate a turbine section casing, wherein the outer shroud component includes at least one airway for ingesting an airstream. Also included is an inner shroud component disposed radially inward of, and fixedly connected to, the outer shroud component, wherein the inner shroud component includes a plurality of microchannels extending in at least one of a circumferential direction and an axial direction for cooling the inner shroud component with the airstream from the at least one airway.
摘要翻译：用于燃气涡轮机系统的涡轮机罩冷却组件包括设置在燃气涡轮机系统的涡轮机部分内并且靠近涡轮部分壳体的外护罩部件，其中外护罩部件包括用于摄取气流的至少一个气道。还包括内护罩部件，其设置在外护罩部件的径向内侧并且固定地连接到外护罩部件上，其中内护罩部件包括沿圆周方向和轴向方向中的至少一个延伸的多个微通道，用于冷却内护罩具有来自至少一个气道的气流的部件。

76. 发明授权

US09080451B2 Airfoil 有权
标题翻译：翼型
公开(公告)号：US09080451B2
公开(公告)日：2015-07-14
申请号：US13535540
申请日：2012-06-28
申请人： Stanley Frank Simpson , Benjamin Paul Lacy
发明人： Stanley Frank Simpson , Benjamin Paul Lacy
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/305 , F05D2240/306 , F05D2260/202 , F05D2260/204
摘要： An airfoil includes an interior surface, an exterior surface opposed to the interior surface, a pressure side, a suction side opposed to the pressure side, a stagnation line between the pressure and suction sides, and a trailing edge between the pressure and suction sides and downstream from the stagnation line. A first column of overlapping stagnation trench segments is on the exterior surface, and the stagnation line passes through at least a portion of each of the overlapping stagnation trench segments. At least one cooling passage in each stagnation trench segment provides fluid communication from the interior surface to the exterior surface.
摘要翻译：翼型件包括内表面，与内表面相对的外表面，压力侧，与压力侧相对的吸入侧，压力侧和吸力侧之间的停滞线以及压力侧和吸力侧之间的后缘以及下游停滞线。重叠停滞沟槽段的第一列在外表面上，停滞线穿过每个重叠停滞槽段的至少一部分。每个停滞槽段中的至少一个冷却通道提供从内表面到外表面的流体连通。

77. 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。

78. 发明授权

US08870535B2 Airfoil 有权
标题翻译：翼型
公开(公告)号：US08870535B2
公开(公告)日：2014-10-28
申请号：US13349852
申请日：2012-01-13
申请人： Benjamin Paul Lacy
发明人： Benjamin Paul Lacy
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2240/303 , F05D2240/81 , F05D2250/324 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes a platform and an exterior surface connected to the platform. A plurality of trench segments are on the exterior surface, and a single cooling passage in each trench segment supplies a cooling media to the exterior surface.
摘要翻译：翼型件包括平台和连接到平台的外表面。多个沟槽段在外表面上，并且每个沟槽段中的单个冷却通道将冷却介质供应到外表面。

79. 发明授权

US08870523B2 Method for manufacturing a hot gas path component and hot gas path turbine component 有权
标题翻译：热气路径部件和热气路径涡轮部件的制造方法
公开(公告)号：US08870523B2
公开(公告)日：2014-10-28
申请号：US13042167
申请日：2011-03-07
申请人： Srikanth Chandrudu Kottilingam , David Vincent Bucci , Benjamin Paul Lacy , Kathleen Blanche Morey , Brian Lee Tollison , Patrick Thomas Walsh
发明人： Srikanth Chandrudu Kottilingam , David Vincent Bucci , Benjamin Paul Lacy , Kathleen Blanche Morey , Brian Lee Tollison , Patrick Thomas Walsh
IPC分类号： F01D5/14 , B23P15/04 , F02C7/00 , F01D9/04 , B23K31/02
CPC分类号： F02C7/00 , B23K31/02 , F01D9/04 , F05D2230/237 , F05D2240/11 , F05D2260/20 , Y10T29/49323
摘要： According to one aspect of the invention, a method for manufacturing a hot gas path component of a turbine is provided, the method including forming cooling channels in a surface of a member. The method also includes disposing a layer on the surface of the member to enclose the cooling channels, the layer being disposed on a portion of the member to be cooled and bonding the layer to the surface, wherein bonding comprises heating the member and the layer.
摘要翻译：根据本发明的一个方面，提供了一种用于制造涡轮机的热气体通道部件的方法，所述方法包括在部件的表面中形成冷却通道。该方法还包括在构件的表面上设置一层以封闭冷却通道，该层设置在要冷却的构件的一部分上，并将该层粘合到该表面上，其中，接合包括加热该构件和该层。

80. 发明授权

US08753083B2 Curved cooling passages for a turbine component 有权
标题翻译：用于涡轮机部件的弯曲冷却通道
公开(公告)号：US08753083B2
公开(公告)日：2014-06-17
申请号：US13006914
申请日：2011-01-14
申请人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan
发明人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D9/02 , F05D2250/71 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A turbine component having a curved cooling passage is disclosed. The turbine component may generally comprise an airfoil having a base and a tip disposed opposite the base. The airfoil may further include a pressure side and a suction side extending between a leading edge and a trailing edge. An airfoil cooling circuit may be at least partially disposed within the airfoil and may be configured to direct a cooling medium through the airfoil. The curved cooling passage may generally be in flow communication with the airfoil cooling circuit such that the cooling medium flowing through the airfoil cooling circuit may be directed into the cooling passage. Additionally, the curved cooling passage may generally extend lengthwise within the airfoil between the leading and trialing edges along at least a portion of one of the pressure side and the suction side of the airfoil.
摘要翻译：公开了一种具有弯曲冷却通道的涡轮机部件。涡轮机部件通常可以包括具有基部和与基部相对设置的尖端的翼型件。翼型件还可以包括在前缘和后缘之间延伸的压力侧和吸力侧。翼型件冷却回路可以至少部分地设置在翼型内，并且可以被配置成引导冷却介质通过翼型件。弯曲的冷却通道通常可以与翼型件冷却回路流动连通，使得流过翼型件冷却回路的冷却介质可以被引导到冷却通道中。此外，弯曲的冷却通道可以沿翼型的压力侧和吸力侧中的一个的至少一部分大体上在翼型之间在引导和试验边缘之间的翼型内延伸。

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