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公开(公告)号：US09416675B2
公开(公告)日：2016-08-16
申请号：US14164707
申请日：2014-01-27
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Christopher Donald Porter , David Edward Schick , David Wayne Weber
CPC classification number: F01D11/005 , F01D9/023 , F01D11/003 , F05D2240/11 , F05D2240/55 , F16J15/02 , F16J15/061 , F16J15/126
Abstract: Sealing device for providing seals between adjacent components, and turbomachines utilizing such sealing devices, are provided. A sealing device includes a seal plate insertable between the adjacent components, the seal plate comprising a first face and an opposing second face. The sealing device further includes a plurality of pins extending from one of the first face or the second face, the plurality of pins configured to space the one of the first face or the second face from contact surfaces of the adjacent components.
Abstract translation: 提供了用于在相邻部件之间提供密封的密封装置，以及利用这种密封装置的涡轮机。 密封装置包括可插入相邻部件之间的密封板，密封板包括第一面和相对的第二面。 所述密封装置还包括从所述第一面或所述第二面中的一个延伸的多个销，所述多个销用于将所述第一面或所述第二面中的一个从所述相邻部件的接触表面间隔开。
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12.发明申请GAS TURBINE TRANSITION PIECE AFT FRAME ASSEMBLIES WITH COOLING CHANNELS AND METHODS FOR MANUFACTURING THE SAME 有权具有冷却通道的气体涡轮转换丝杠组合框架及其制造方法公开(公告)号：US20150369068A1
公开(公告)日：2015-12-24
申请号：US14090832
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Srikanth Chandrudu Kottilingam , Benjamin Paul Lacy , Brian Lee Tollison , David Edward Schick
IPC: F01D9/02
CPC classification number: F01D9/023 , B22F5/10 , B22F7/08 , C22C1/0433 , C22C19/056 , C22C19/057 , F01D25/12 , F05D2220/32 , F05D2230/22 , F05D2230/60 , F05D2230/90 , F05D2260/201 , F23R3/60 , F23R2900/00018 , Y02T50/671 , Y02T50/676
Abstract: Aft frame assemblies for a gas turbine transition pieces include a body comprising an exterior surface and a plurality of interior surfaces, one or more exterior cooling holes disposed on the exterior surface of the body for capturing compressor discharge air outside of the transition piece, and a supplemental component bonded to at least one of the plurality of interior surfaces of the body. At least one cooling channel is at least partially defined by the supplemental component and the interior surface that the supplemental component is bonded to, wherein the at least one cooling channel fluidly connects at least one of the one or more exterior cooling holes to one or more interior cooling outlets that discharge the compressor discharge air captured from the at least one of the one or more exterior cooling holes.
Abstract translation: 用于燃气涡轮机过渡件的后框架组件包括：主体，其包括外表面和多个内表面;一个或多个外部冷却孔，设置在主体的外表面上，用于捕获过渡件外部的压缩机排出空气;以及 补充部件结合到身体的多个内表面中的至少一个。 至少一个冷却通道至少部分地由补充部件和附加部件结合到的内表面限定，其中至少一个冷却通道将一个或多个外部冷却孔中的至少一个流体连接到一个或多个 内部冷却出口，其排出从一个或多个外部冷却孔中的至少一个捕获的压缩机排放空气。
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公开(公告)号：US20150218962A1
公开(公告)日：2015-08-06
申请号：US14173949
申请日：2014-02-06
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Benjamin Paul Lacy , Aaron Ezekiel Smith , Dustin Michael Earnhardt
CPC classification number: B22C7/02 , B22C9/04 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2240/81 , F05D2260/204
Abstract: A core for forming micro channels within a turbine component is provided. The core includes a base comprising a first side and a second side; and a core assembly coupled to the second side. The core assembly further includes a plurality of channel members, wherein each channel member has a first end, a second end, and a channel body coupled to and extending between said first end and said second end. The channel body includes a channel shape configured to form the micro channels within the turbine component.
Abstract translation: 提供了一种用于在涡轮机部件内形成微通道的芯。 芯部包括一个包括第一面和第二面的基底; 以及耦合到第二侧的芯组件。 芯组件还包括多个通道构件，其中每个通道构件具有第一端，第二端和与所述第一端和所述第二端连接并在其之间延伸的通道体。 通道体包括被配置为在涡轮部件内形成微通道的通道形状。
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公开(公告)号：US20150086408A1
公开(公告)日：2015-03-26
申请号：US14037887
申请日：2013-09-26
Applicant: General Electric Company
Inventor： Srikanth Chandrudu KOTTILINGAM , Benjamin Paul Lacy , Carlos Miguel Miranda , David Edward Schick
CPC classification number: B22F5/04 , B22F3/1055 , B22F5/10 , B22F7/062 , B22F7/08 , B22F2005/005 , B22F2998/10 , B22F2999/00 , F01D5/187 , F05D2230/30 , F05D2260/204 , F05D2260/22141 , Y02P10/295 , B22F3/15 , B22F2003/248 , C23C28/00 , B22D25/00 , B23K1/00
Abstract: A method of manufacturing a component and a method of thermal management are provided. The methods include forming at least one portion of the component, printing a cooling member of the component and attaching the at least one portion to the cooling member of the component. The cooling member includes at least one cooling feature. The at least one cooling feature includes at least one cooling channel adjacent to a surface of the component, wherein printing allows for near-net shape geometry of the cooling member with the at least one cooling channel being located within a range of about 127 (0.005 inches) to about 762 micrometers (0.030 inches) from the surface of the component. The method of thermal management also includes transporting a fluid through at least one fluid pathway defined by the at least one cooling channel within the component to cool the component.
Abstract translation: 提供了一种制造组件的方法和热管理方法。 所述方法包括形成部件的至少一部分，印刷部件的冷却部件并将该至少一个部分附接到部件的冷却部件。 冷却构件包括至少一个冷却特征。 所述至少一个冷却特征包括与所述部件的表面相邻的至少一个冷却通道，其中所述打印允许所述冷却部件的近净形几何形状，所述至少一个冷却通道位于约127（0.005 英寸）到组件表面的约762微米（0.030英寸）。 热管理的方法还包括通过由部件内的至少一个冷却通道限定的至少一个流体路径输送流体以冷却部件。
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公开(公告)号：US20140321994A1
公开(公告)日：2014-10-30
申请号：US13853556
申请日：2013-03-29
Applicant: General Electric Company
Inventor： Brian Gene Brzek , Victor John Morgan , Benjamin Paul Lacy
CPC classification number: F01D25/12 , F01D5/183 , F01D5/186 , F01D9/02 , F01D9/041 , F05D2300/514 , F05D2300/612 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.
Abstract translation: 公开了一种用于涡轮机系统的热气体路径部件。 热气体路径部件包括壳体和一个或多个多孔介质，其具有外表面和内表面并且邻近壳体定位。 一个或多个多孔介质被配置为包括在轴向方向，径向方向，轴向和径向方向，轴向和圆周方向，径向和圆周方向或轴向，径向和 圆周方向，多孔介质位于壳体附近。 一个或多个多孔介质还被构造成控制冷却介质的轴向，径向，轴向和径向，轴向和周向的径向和周向或轴向的径向和周向流动 流过
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Patent Agency Ranking
公开(公告)号：US20140237784A1
公开(公告)日：2014-08-28
申请号：US13774275
申请日：2013-02-22
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Benjamin Paul Lacy , Paul Stephen Dimascio , Srikanth Chandrudu Kottilingam , David Edward Schick
CPC classification number: B23P15/00 , B23P15/02 , B23P17/00 , B23P2700/13 , F23R3/002 , F23R2900/00018 , Y10T29/302 , Y10T29/49234 , Y10T29/4935 , Y10T29/49906
Abstract: A method of forming a microchannel cooled component is provided. The method includes forming at least one microchannel within a surface of a relatively planar plate. The method also includes placing a relatively planar cover member over the surface having the at least one microchannel formed therein. The method further includes adhering the relatively planar cover member to the relatively planar plate. The method yet further includes curving the microchannel cooled component by pressing the relatively planar cover member with a forming component for at least a portion of a time period of adhering the relatively planar cover member to the relatively planar plate.
Abstract translation: 提供了形成微通道冷却部件的方法。 该方法包括在相对平面的板的表面内形成至少一个微通道。 该方法还包括将相对平坦的覆盖部件放置在其上形成有至少一个微通道的表面上。 该方法还包括将相对平坦的盖构件粘附到相对平面的板上。 该方法还包括通过用相对平面的覆盖构件将成形部件按压至少一部分将相对平面的盖构件粘附到相对平面的板的时间段来弯曲微通道冷却部件。
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公开(公告)号：US11519281B2
公开(公告)日：2022-12-06
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
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公开(公告)号：US11434767B2
公开(公告)日：2022-09-06
申请号：US16663941
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Lyndsay Marie Kibler , Brad Wilson VanTassel , Benjamin Paul Lacy , Zachary John Snider , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
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公开(公告)号：US20210270141A1
公开(公告)日：2021-09-02
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
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公开(公告)号：US11015481B2
公开(公告)日：2021-05-25
申请号：US16015268
申请日：2018-06-22
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy
Abstract: A cooled structure has a leading edge, a trailing edge, a first side portion orthogonal to each of the leading and trailing edge, and a second side portion opposite the first side portion and substantially orthogonal to each of the leading and trailing edge. The cooled structure includes a substrate surface defined by boundaries including the leading edge, trailing edge, first side and second side portion. A first set of cooling channels beneath the substrate surface extends from a first set of inlets proximate to the first side portion to a first set of exits proximate to the second side portion. A second set of cooling channels beneath the substrate surface extends from a second set of inlets proximate to the second side portion to a second set of exits proximate to the first side portion. Each first inlet overlaps with an exit of the second set of exits.
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