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1. 发明授权

US10760430B2 Adaptively opening backup cooling pathway 有权
公开(公告)号：US10760430B2
公开(公告)日：2020-09-01
申请号：US15609598
申请日：2017-05-31
申请人： General Electric Company
发明人： Benjamin Paul Lacy , Brian Peter Arness , Victor John Morgan , Stephen William Tesh
IPC分类号： F01D5/08 , F01D5/18 , F01D9/04 , F01D9/06
摘要： A hot gas path (HGP) component of an industrial machine includes primary and secondary cooling pathways. A body includes an internal cooling circuit carrying a cooling medium. A primary cooling pathway is spaced internally in the body and carries a primary flow of a cooling medium from an internal cooling circuit. A secondary cooling pathway is in the body and in fluid communication with an internal cooling circuit. The secondary cooling pathway is fluidly incommunicative and spaced internally from the primary cooling pathway. In response to an overheating event occurring, the secondary cooling pathway opens to allow a secondary flow of cooling medium through to the outer surface of the body and/or the primary cooling pathway. The primary flow flows in the primary cooling pathway prior to the overheating event, and the secondary flow of cooling medium does not flow until after an opening of the secondary cooling pathway.

2. 发明授权

US10655489B2 Systems and methods for assembling flow path components 有权
公开(公告)号：US10655489B2
公开(公告)日：2020-05-19
申请号：US15862520
申请日：2018-01-04
申请人： GENERAL ELECTRIC COMPANY
发明人： Neelesh Nandkumar Sarawate , Christopher Edward Wolfe , Victor John Morgan , Jason Ray Gregg
IPC分类号： F01D11/00 , F01D9/04
摘要： An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

3. 发明授权

US10100666B2 Hot gas path component for turbine system 有权
公开(公告)号：US10100666B2
公开(公告)日：2018-10-16
申请号：US13853556
申请日：2013-03-29
申请人： General Electric Company
发明人： Brian Gene Brzek , Victor John Morgan , Benjamin Paul Lacy
IPC分类号： F01D25/12 , F01D5/14 , F01D9/02 , F01D5/18 , F01D9/04
摘要： 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.

4. 发明授权

US09719420B2 Gas turbine component and process for producing gas turbine component 有权
公开(公告)号：US09719420B2
公开(公告)日：2017-08-01
申请号：US14292969
申请日：2014-06-02
申请人： GENERAL ELECTRIC COMPANY
发明人： Paul Stephen DiMascio , Victor John Morgan , Jason Robert Parolini , Glenn Curtis Taxacher , Frederic Woodrow Roberts, Jr. , Jacob John Kittleson , John McConnell Delvaux
IPC分类号： F02C7/00 , B23K1/00 , B23P6/00 , B24B33/00 , C04B41/00 , C04B41/45 , C04B41/50 , C04B41/53 , C04B41/85 , C04B41/91 , C04B41/87 , C04B41/88 , C04B41/51 , C23C16/24
CPC分类号： F02C7/00 , B23K1/0018 , B23P6/002 , B23P6/007 , B24B33/00 , C04B41/009 , C04B41/4531 , C04B41/5025 , C04B41/5096 , C04B41/5144 , C04B41/53 , C04B41/85 , C04B41/87 , C04B41/88 , C04B41/91 , C23C16/24 , F05D2230/30 , F05D2230/90 , F05D2300/6033 , Y10T156/10 , Y10T428/24355 , C04B35/00 , C04B35/80 , C04B41/4529 , C04B41/4539 , C04B41/5133 , C04B41/0072
摘要： A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.

5. 发明申请

US20170037731A1 COOLING STRUCTURE FOR HOT-GAS PATH COMPONENTS WITH METHODS OF FABRICATION 有权
标题翻译：具有制造方法的热气路径组件的冷却结构
公开(公告)号：US20170037731A1
公开(公告)日：2017-02-09
申请号：US14818695
申请日：2015-08-05
申请人： General Electric Company
发明人： Victor John Morgan , George Andrew Gergely , Frederic Woodrow Roberts, JR. , Aaron Ezekiel Smith
IPC分类号： F01D5/18 , B23P15/02 , F01D9/06
CPC分类号： F01D5/187 , B23P15/02 , F01D9/065 , F05D2240/81 , F05D2250/314 , F05D2250/75 , F05D2260/2212 , F05D2260/2214
摘要： Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.
摘要翻译：本公开的实施例提供了用于热气路径（HGP）部件的部件及其形成方法。根据本公开的结构可以包括：HGP部件，其从涡轮机的转子轴线径向延伸，所述HGP部件包括锥形边缘; 多个第一通道，其与HGP部件的预冷却区域流体连通，并且延伸穿过位于预冷却区域和锥形边缘之间的侧壁; 以及多个第二通道，其至少延伸穿过所述锥形边缘，其中所述多个第二通道中的每一个与所述操作流体的流动路径和所述多个第一通道的至少一个通道流体连通，并且其中至少多个第二通道中的一个从多个第一通道的每个通道径向移位。

6. 发明授权

US09482249B2 Three-dimensional printing process, swirling device and thermal management process 有权
标题翻译：三维印刷工艺，旋转装置和热管理流程
公开(公告)号：US09482249B2
公开(公告)日：2016-11-01
申请号：US14020997
申请日：2013-09-09
申请人： GENERAL ELECTRIC COMPANY
发明人： Srikanth Chandrudu Kottilingam , Victor John Morgan , Benjamin Paul Lacy , John Wesley Harris, Jr. , David Edward Schick
IPC分类号： F15D1/00 , B22F3/105 , B22F5/00 , B33Y10/00 , F01D5/18 , F01D11/24 , B29C67/00 , B33Y80/00 , F25B9/04
CPC分类号： F15D1/0015 , B22F3/1055 , B22F5/009 , B29C64/153 , B33Y10/00 , B33Y80/00 , F01D5/18 , F01D11/24 , F05D2240/127 , F05D2240/81 , F05D2260/204 , F05D2260/221 , F05D2260/2212 , F25B9/04 , Y02P10/295 , Y10T137/2087
摘要： A three-dimensional printing process, a swirling device, and a thermal management process are disclosed. The three-dimensional printing process includes distributing a material to a selected region, selectively laser melting the material, and forming a swirling device from the material. The swirling device is printed by selective laser melting. The thermal management process includes providing an article having a swirling device printed by selective laser melting, and cooling a portion of the article by transporting air through the swirling device.
摘要翻译：公开了三维打印处理，旋转装置和热管理过程。三维印刷工艺包括将材料分配到所选择的区域，选择性地激光熔化材料，以及从材料形成旋转装置。旋转装置通过选择性激光熔化印刷。热管理方法包括提供具有通过选择性激光熔化印刷的旋转装置的制品，以及通过将空气输送通过旋转装置来冷却制品的一部分。

7. 发明申请

US20160024951A1 FLEXIBLE LAYERED SEAL FOR TURBOMACHINERY 审中-公开
标题翻译：柔性层封装用于涡轮机
公开(公告)号：US20160024951A1
公开(公告)日：2016-01-28
申请号：US14337453
申请日：2014-07-22
申请人： General Electric Company
发明人： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
IPC分类号： F01D11/00 , F16J15/02
CPC分类号： F01D11/005 , F05D2240/59 , F16J15/02 , F16J15/0812
摘要： The present application provides seal assemblies having improved flexibility for reducing leakages between adjacent misaligned components of turbomachinery. The seal assemblies include a first outer shim formed of a flexible permeable material and a second outer shim formed of a substantially impervious material. At least the second outer shim is configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the first and second outer shims. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to meet operating requirements associated with turbomachinery. A turbomachine including the seal assembly is provided.
摘要翻译：本申请提供了具有改进的柔性的密封组件，用于减少涡轮机械的相邻不对准部件之间的泄漏。密封组件包括由柔性可渗透材料形成的第一外垫片和由基本上不可渗透的材料形成的第二外垫片。至少第二外垫片构造成用于与相邻部件的密封槽密封接合。密封组件还可以包括位于第一和第二外垫片之间的内垫片和填料层中的至少一个。密封组件可以足够灵活以考虑相邻部件之间的不对准，足够坚硬以满足组装要求，并且足够坚固以满足与涡轮机械相关的操作要求。提供包括密封组件的涡轮机。

8. 发明申请

US20150118042A1 METHOD AND SYSTEM FOR PROVIDING SEALING IN GAS TURBINES 审中-公开
标题翻译：用于在气体涡轮机中提供密封的方法和系统
公开(公告)号：US20150118042A1
公开(公告)日：2015-04-30
申请号：US14063269
申请日：2013-10-25
申请人： General Electric Company
发明人： Victor John Morgan , Aaron Ezekiel Smith , David Wayne Weber
IPC分类号： F01D11/00
CPC分类号： F01D11/005 , F01D11/003 , F01D11/006 , F01D11/008
摘要： A gas turbine system is provided that includes a compressor section, a combustor assembly coupled to the compressor section, and a turbine section coupled to the compressor section. At least one of the combustor assembly and the turbine section includes a sealing sub-system for use in sealing between a first component and a second component. A first component defines a first seal member receiving region oriented between a higher-temperature gas region and a cooler-temperature gas region. A second component adjacent the first component defines a second seal member receiving region oriented adjacent the first seal member receiving region. The sealing system includes first and second end walls defined in at least one of the first and second seal member receiving regions. A seal member is oriented within the first and second seal member receiving regions, and includes at least a first layer defining at least a first resilient seal end portion that engages one of the first and second end walls.
摘要翻译：提供了一种燃气轮机系统，其包括压缩机部分，联接到压缩机部分的燃烧器组件和联接到压缩机部分的涡轮部分。燃烧器组件和涡轮部分中的至少一个包括用于密封第一部件和第二部件之间的密封子系统。第一部件限定在较高温度气体区域和较冷温度气体区域之间定向的第一密封构件接收区域。与第一部件相邻的第二部件限定了邻近第一密封件接收区域定向的第二密封件接收区域。密封系统包括限定在第一和第二密封构件接收区域中的至少一个中的第一和第二端壁。密封构件定位在第一和第二密封构件接收区域内，并且包括限定至少第一弹性密封端部的至少第一层，该第一层限定第一和第二端壁中的一个。

9. 发明申请

US20150096305A1 METHOD AND SYSTEM FOR PROVIDING COOLING FOR TURBINE COMPONENTS 有权
标题翻译：用于提供涡轮机组件冷却的方法和系统
公开(公告)号：US20150096305A1
公开(公告)日：2015-04-09
申请号：US14046437
申请日：2013-10-04
申请人： General Electric Company
发明人： Victor John Morgan , John Wesley Harris, Jr. , Michael James Healy , Aaron Ezekiel Smith , Brian Gene Brzek , Donald Earl Floyd, II
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/183 , F01D5/186 , F01D5/187 , F01D9/065 , F05D2230/21 , F05D2230/90 , F05D2240/122 , F05D2260/202 , F05D2260/204 , F05D2260/22141 , F05D2300/612
摘要： A method and system for providing cooling of a turbine component that includes a region to be cooled is provided. A recess is defined within the region to be cooled, and includes an inner face. At least one support projection extends from the inner face. The at least one support projection includes a free end. A cover is coupled to the region to be cooled, such that an inner surface of the cover is coupled to the free end of the at least one support projection, such that at least one cooling fluid passage is defined within the region to be cooled.
摘要翻译：提供了一种用于提供包括待冷却区域的涡轮机部件的冷却的方法和系统。在待冷却的区域内限定凹部，并且包括内表面。至少一个支撑突起从内表面延伸。所述至少一个支撑突起包括自由端。盖被联接到要冷却的区域，使得盖的内表面联接到至少一个支撑突起的自由端，使得至少一个冷却流体通道限定在待冷却的区域内。

10. 发明申请

US20140099183A1 TURBINE COMPONENTS WITH PASSIVE COOLING PATHWAYS 有权
标题翻译：涡轮组件与无源冷却路径
公开(公告)号：US20140099183A1
公开(公告)日：2014-04-10
申请号：US13645729
申请日：2012-10-05
申请人： GENERAL ELECTRIC COMPANY
发明人： Victor John Morgan , Stephen Gerard Pope , Jacob Kittleson , Lawrence Matthew Levy
IPC分类号： F01D25/12 , F01D5/18 , F01D9/02
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F05D2230/10 , F05D2230/50 , F05D2300/611
摘要： The present application provides a turbine component for use in a hot gas path of a gas turbine. The turbine component may include an outer surface, an internal cooling circuit, a number of cooling pathways in communication with the internal cooling circuit and extending through the outer surface, and a number of adaptive cooling pathways in communication with the internal cooling circuit and extending through the outer surface. The adaptive cooling pathways may include a high temperature compound therein.
摘要翻译：本申请提供了一种在燃气轮机的热气路径中使用的涡轮机部件。涡轮机部件可以包括外表面，内部冷却回路，与内部冷却回路连通并延伸穿过外表面的多个冷却通路，以及与内部冷却回路连通并延伸通过的多个自适应冷却通道外表面。适应性冷却途径可包括其中的高温化合物。

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