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71. 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。

72. 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。

73. 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。

74. 发明申请

US20140003960A1 AIRFOIL 有权
标题翻译：翼型
公开(公告)号：US20140003960A1
公开(公告)日：2014-01-02
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。

75. 发明申请

US20130315748A1 COOLING STRUCTURES IN THE TIPS OF TURBINE ROTOR BLADES 有权
标题翻译：涡轮转子叶片的冷却结构
公开(公告)号：US20130315748A1
公开(公告)日：2013-11-28
申请号：US13479663
申请日：2012-05-24
申请人： Benjamin Paul Lacy , Brian Peter Arness , Xiuzhang James Zhang
发明人： Benjamin Paul Lacy , Brian Peter Arness , Xiuzhang James Zhang
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/186 , F05D2260/204
摘要： A turbine rotor blade used in a gas turbine engine, which includes an airfoil having a tip at an outer radial edge, is described. The airfoil includes a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge of the airfoil, the pressure sidewall and the suction sidewall extending from a root to the tip. The tip includes a tip plate and, disposed along a periphery of the tip plate, a rail. The rail includes a microchannel connected to a coolant source.
摘要翻译：描述了一种在燃气涡轮发动机中使用的涡轮转子叶片，其包括在外径向边缘处具有尖端的翼型件。翼型件包括压力侧壁和抽吸侧壁，该侧壁在翼型的前缘和后缘处连接在一起，压力侧壁和吸力侧壁从根部延伸到尖端。尖端包括尖端板，并且沿着尖端板的周边布置有轨道。导轨包括连接到冷却剂源的微通道。

76. 发明授权

US08453454B2 Coannular oil injection nozzle 有权
标题翻译：管状注油嘴
公开(公告)号：US08453454B2
公开(公告)日：2013-06-04
申请号：US12759794
申请日：2010-04-14
申请人： Benjamin Paul Lacy , Thomas Edward Johnson , William David York , Baifang Zuo
发明人： Benjamin Paul Lacy , Thomas Edward Johnson , William David York , Baifang Zuo
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23D11/12 , F23R3/20 , F23R3/36
摘要： A premixer is provided and includes a peripheral wall defining a mixing chamber therein through which a flow path for a fluid is defined, a nozzle including an annular splitter plate disposed in the flow path within the mixing chamber, the splitter plate including a trailing edge defined in relation to a predominant direction of fluid flow along the flow path and being formed to define a fuel line therein, which is receptive of oil fuel and an annular array of fuel injectors disposed at the trailing edge, which are each fluidly communicative with the fuel line and configured to inject at least the oil fuel into the flow path with the oil fuel being substantially atomized upon injection or substantially immediately after the injection by interaction with the fluid flowing along the flow path.
摘要翻译：提供预混合器并且包括在其中限定混合室的外围壁，通过该混合室限定用于流体的流动路径，喷嘴，其包括设置在混合室内的流动路径中的环形分离板，分离板包括限定的后缘相对于沿着流动路径的流体流动的主要方向并且被形成为在其中限定其中容纳油燃料的燃料管线和设置在后缘处的燃料喷射器的环形阵列，其各自与燃料流体连通并且构造成至少将油燃料喷射到流动路径中，其中油燃料在注射时基本上雾化，或者基本上在注射之后立即与沿着流动路径流动的流体相互作用。

77. 发明申请

US20130094944A1 BUCKET ASSEMBLY FOR TURBINE SYSTEM 有权
标题翻译：用于涡轮机系统的BUCKET装配
公开(公告)号：US20130094944A1
公开(公告)日：2013-04-18
申请号：US13271751
申请日：2011-10-12
申请人： Benjamin Paul Lacy , Anthony Louis Giglio
发明人： Benjamin Paul Lacy , Anthony Louis Giglio
IPC分类号： F01D11/08
CPC分类号： F01D5/225 , F05D2230/31 , F05D2250/294 , F05D2260/204
摘要： A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface.
摘要翻译：公开了一种铲斗组合件。铲斗组件包括具有大致空气动力学轮廓并限定尖端的翼型件和从翼型件大致径向向内延伸的下主体部分。铲斗组件还包括设置在翼型件的尖端上并包括主体和轨道的尖端护罩。导轨包括外表面。外表面限定了一个微通道。铲斗组件还包括构造在外表面上的覆盖层。

78. 发明授权

US08333075B2 Gas turbine premixer with internal cooling 有权
标题翻译：燃气轮机预混合器内部冷却
公开(公告)号：US08333075B2
公开(公告)日：2012-12-18
申请号：US12425293
申请日：2009-04-16
申请人： William David York , Thomas Edward Johnson , Benjamin Paul Lacy , Christian Xavier Stevenson
发明人： William David York , Thomas Edward Johnson , Benjamin Paul Lacy , Christian Xavier Stevenson
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23R3/14 , F23R3/283
摘要： A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction through a substantial length of the swirl vane.
摘要翻译：一种包括涡轮燃料喷嘴的系统，其包括空燃料预混合器。空燃料预混合包括涡流叶片，其构造成沿下游方向旋转燃料和空气，其中涡流叶片包括从上游方向的下游端部通过旋转叶片的相当长度的内部冷却剂路径。

79. 发明申请

US20120156054A1 TURBINE COMPONENT WITH NEAR-SURFACE COOLING PASSAGE AND PROCESS THEREFOR 审中-公开
标题翻译：具有近表面冷却通风的涡轮机组件及其过程
公开(公告)号：US20120156054A1
公开(公告)日：2012-06-21
申请号：US12968410
申请日：2010-12-15
申请人： Benjamin Paul Lacy , David Vincent Bucci , Srikanth Chandrudu Kottilingam , Dennis William Cavanaugh
发明人： Benjamin Paul Lacy , David Vincent Bucci , Srikanth Chandrudu Kottilingam , Dennis William Cavanaugh
IPC分类号： F01D5/18 , B22D23/00 , B05D3/12
CPC分类号： F01D5/288 , B23P2700/06 , C23C28/321 , C23C28/3215 , C23C28/3455 , F01D5/18 , F01D5/186 , F05D2230/20 , Y02T50/673 , Y02T50/676 , Y02T50/6765
摘要： A process for creating a near-surface cooling passage in an air-cooled turbomachine component. The process entails forming a channel in a surface of a surface region of the component so that the channel is open at the surface and fluidically connected to a first cooling passages within the component. A metallic layer is then deposited on the surface and over the channel without filling the channel. The metallic layer closes the channel at the surface of the surface region to define therewith a second cooling passage within the component that is fluidically connected to the first cooling passages. A coating system is then deposited on the metallic layer to define an outermost surface of the component. The second cooling passage is closer to the outermost surface of the component than the first cooling passages.
摘要翻译：一种用于在空气冷却涡轮机组件中形成近地面冷却通道的方法。该过程需要在部件的表面区域的表面中形成通道，使得通道在表面处是开放的并且与部件内的第一冷却通道流体连接。然后将金属层沉积在表面上并在通道上沉积，而不填充通道。金属层封闭在表面区域的表面处的通道，以限定该部件内的与第一冷却通道流体连接的第二冷却通道。然后将涂层系统沉积在金属层上以限定该组件的最外表面。第二冷却通道比第一冷却通道更靠近部件的最外表面。

80. 发明申请

US20120085103A1 SHIM FOR SEALING TRANSITION PIECES 有权
标题翻译： SHIM密封过渡片
公开(公告)号：US20120085103A1
公开(公告)日：2012-04-12
申请号：US12900072
申请日：2010-10-07
申请人： Benjamin Paul Lacy , Mehmet Demiroglu , Neelesh Nandkumar Sarawate
发明人： Benjamin Paul Lacy , Mehmet Demiroglu , Neelesh Nandkumar Sarawate
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F01D11/003 , F16J15/0887
摘要： According to one aspect of the invention, a shim for sealing two adjacent turbine transition pieces is disclosed. The shim includes a circumferential member that includes a first lateral flange and a second lateral flange. Further, the first and second lateral flanges each comprise a tab configured to mate to a first surface plane and the first and second lateral flanges are configured to mate to a second surface plane, wherein the first and second surface planes are substantially parallel. In addition, the shim includes a first flange extending substantially perpendicular from the circumferential member.
摘要翻译：根据本发明的一个方面，公开了一种用于密封两个相邻涡轮机过渡件的垫片。垫片包括周向构件，其包括第一侧向凸缘和第二侧向凸缘。此外，第一和第二横向凸缘各自包括配置成与第一表面平面配合的突出部，并且第一和第二横向凸缘构造成与第二表面平面配合，其中第一和第二表面基本平行。此外，垫片包括从圆周构件基本上垂直延伸的第一凸缘。

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