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1.发明申请公开(公告)号：US20170101873A1
公开(公告)日：2017-04-13
申请号：US14878084
申请日：2015-10-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor John MORGAN , Jacob John KITTLESON , Andres Jose GARCIA-CRESPO , Benjamin Paul LACY
CPC classification number: F01D5/282 , B32B18/00 , C04B35/573 , C04B35/6269 , C04B35/806 , C04B2235/5244 , C04B2235/5248 , C04B2235/5268 , C04B2235/612 , C04B2235/614 , C04B2235/616 , C04B2237/365 , C04B2237/38 , C04B2237/62 , C23C16/44 , F01D9/02 , F01D25/005 , F05D2220/32 , F05D2230/314 , F05D2240/128 , F05D2240/35 , F05D2300/6033
Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.
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公开(公告)号：US20170044923A1
公开(公告)日：2017-02-16
申请号：US14825636
申请日：2015-08-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Frederic Woodrow ROBERTS , Victor John MORGAN , Matthew Troy HAFNER
CPC classification number: F01D11/22 , F05D2240/11 , F05D2260/50 , F05D2300/6033
Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.
Abstract translation: 公开了一种涡轮机护罩组件，其包括具有与热气体路径相邻的表面的内护罩，外护罩和偏置装置。 偏压装置被布置和设置成沿着远离热气体路径的方向偏压内护罩，将内护罩装载到外护罩。 在另一个实施例中，偏置装置是一弹簧偏压装置，其包括至少一个波纹管，至少一个推力活塞或至少一个波纹管和至少一个推力活塞的组合。 公开了一种用于装载涡轮机护罩组件的方法，包括：将具有与热气体路径相邻的表面的内护罩偏压在远离热气路径的方向朝向外护罩的偏压，其中偏压内护罩包括由 偏置装置。
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3.发明申请THREE-DIMENSIONAL PRINTING PROCESS, SWIRLING DEVICE AND THERMAL MANAGEMENT PROCESS 有权三维印刷工艺，开发设备和热管理流程公开(公告)号：US20150068629A1
公开(公告)日：2015-03-12
申请号：US14020997
申请日：2013-09-09
Applicant: General Electric Company
Inventor： Srikanth Chandrudu KOTTILINGAM , Victor John MORGAN , Benjamin Paul LACY , John Wesley HARRIS, Jr. , David Edward SCHICK
CPC classification number: 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
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20200240273A1
公开(公告)日：2020-07-30
申请号：US16754302
申请日：2017-10-13
Applicant: General Electric Company
Inventor： James Albert TALLMAN , Andrew Philip SHAPIRO , Gary Michael ITZEL , Curtis Alan JOHNSON , Victor John MORGAN , Jacob John KITTLESON , Bradley Thomas RICHARDS
Abstract: A component includes an outer wall that includes an exterior surface, and at least one plenum defined interiorly to the outer wall and configured to receive a cooling fluid therein. The component also includes a coating system disposed on the exterior surface. The coating system has a thickness. The component further includes a plurality of adaptive cooling openings defined in the outer wall. Each of the adaptive cooling openings extends from a first end inflow communication with the at least one plenum, outward through the exterior surface and to a second end covered underneath at least a portion of the thickness of the coating system.
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5.发明申请公开(公告)号：US20150345388A1
公开(公告)日：2015-12-03
申请号：US14292969
申请日：2014-06-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Stephen DIMASCIO , Victor John MORGAN , Jason Robert PAROLINI , Glenn Curtis TAXACHER , Frederic Woodrow ROBERTS, JR. , Jacob John KITTLESON , John McConnell DELVAUX
IPC: F02C7/00 , B23K1/00 , B23P6/00 , C04B41/91 , B24B33/00 , C04B41/00 , C04B41/53 , C04B41/50 , C04B41/45 , C23C16/24 , C04B41/85
CPC classification number: 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
Abstract: 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.
Abstract translation: 提供了陶瓷基复合燃气轮机部件和陶瓷基复合燃气轮机部件的制造方法。 该方法包括改变陶瓷基复合燃气轮机部件的表面以产生表面粗糙度小于6微米的改性表面。 修饰选自由将未增强的基质层施加到表面，在表面上蒸镀硅，珩磨表面，将钎焊膏施加到表面上的技术组合，以及它们的组合。 该组件包括包括小于6微米的表面粗糙度的改性表面。 所述改性表面选自施加到陶瓷基复合燃气轮机部件的表面的未增强基体层，沉积在表面上的硅蒸汽表面，珩磨表面，施加到表面上的钎焊膏及其组合。
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Patent Agency Ranking
公开(公告)号：US20170051627A1
公开(公告)日：2017-02-23
申请号：US14827698
申请日：2015-08-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy HAFNER , Victor John MORGAN , Frederic Woodrow ROBERTS
CPC classification number: F01D11/22 , F01D11/14 , F01D11/20 , F01D25/005 , F01D25/04 , F01D25/08 , F05D2220/32 , F05D2240/11 , F05D2260/52 , F05D2260/96 , F05D2300/17 , F05D2300/171 , F05D2300/502 , F05D2300/6033
Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.
Abstract translation: 公开了一种涡轮机护罩组件，其包括具有与热气体路径相邻的表面的内护罩，外护罩，设置在内护罩和外护罩之间的阻尼块，第一偏压装置和第二偏压装置。 第一偏置装置向内护罩提供第一偏置力，从而朝向热气体路径并远离外护罩的方向偏压内护罩的第一偏转距离。 第二偏压装置向阻尼器块提供第二偏压力，使阻尼器块沿朝向热气体路径并远离外护罩的方向偏置第二偏转距离。 第二偏转距离大于第一偏转距离。
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7.发明申请公开(公告)号：US20160221881A1
公开(公告)日：2016-08-04
申请号：US14612806
申请日：2015-02-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John McConnell DELVAUX , Andres Jose GARCIA-CRESPO , Victor John MORGAN , Jacob John KITTLESON
IPC: C04B35/565 , C04B35/44 , B29C71/04 , C04B35/52
CPC classification number: C04B35/565 , B29C70/545 , B29C71/04 , B29L2031/7504 , B32B3/266 , C04B35/44 , C04B35/52 , F01D5/186 , F01D5/282 , F01D5/284 , F01D5/288 , F01D11/08 , F01D11/24 , F01D25/12 , F01D25/14 , F02C6/06 , F02C6/08 , F05D2230/90 , F05D2240/11 , F05D2260/202 , F05D2260/232 , F05D2270/09 , F05D2270/11 , F05D2270/112 , F05D2300/2261 , F05D2300/6033
Abstract: Components are disclosed which include a CMC substrate having a first surface and a second surface. The first surface is in fluid communication with a compressed, dry fluid, and the second surface is in fluid communication with a wet fluid stream and includes a hermetic coating. The components further include at least one opening extending from the first surface through a portion of the CMC substrate, wherein, upon removal of a fragment of one or both of the hermetic coating and the CMC substrate, the at least one opening selectively permits a flow of the compressed, dry fluid to the second surface. In one embodiment, the component is a gas turbine component, the wet fluid stream is a hot combustion stream, the hermetic coating is an environmental barrier coating, and the flow reduces or eliminates volatilization of the CMC substrate. Methods for forming the components are also disclosed.
Abstract translation: 公开了包括具有第一表面和第二表面的CMC基材的组分。 第一表面与压缩的干燥流体流体连通，并且第二表面与湿流体流流体连通并且包括气密涂层。 所述部件还包括从所述第一表面延伸穿过所述CMC基底的一部分的至少一个开口，其中，在去除所述密封涂层和所述CMC基底中的一个或两者的碎片时，所述至少一个开口选择性地允许流动 的压缩，干燥的流体到第二表面。 在一个实施方案中，组分是燃气轮机组分，湿流体流是热燃烧流，气密涂层是环境屏障涂层，并且该流减少或消除了CMC衬底的挥发。 还公开了用于形成组件的方法。
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公开(公告)号：US20140297053A1
公开(公告)日：2014-10-02
申请号：US13853332
申请日：2013-03-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor John MORGAN , Tomas A. Velez
IPC: G05B13/02
CPC classification number: G05B17/02
Abstract: A method to control an power generation plant including: applying control settings to operate the plant; collecting plant data indicative of the performance of the plant; applying the control settings to a model of the plant; collecting prediction data from the model; comparing the plant data to the predicted data and adjusting the control settings applied to the plant and model; perturbing the control settings and applying the perturbed control settings to operate the plant and the model; collecting perturbed plant data and perturbed prediction data, and modifying the model if the perturbed plant data represents an improvement as compared to the perturbed prediction data.
Abstract translation: 一种控制发电厂的方法，包括：对工厂进行控制设定; 收集指示工厂性能的工厂数据; 将控制设置应用于工厂的模型; 从模型收集预测数据; 将工厂数据与预测数据进行比较，并调整应用于工厂和模型的控制设置; 扰乱控制设置并应用扰动控制设置来操作设备和模型; 收集扰动的植物数据和扰动的预测数据，以及如果扰动的植物数据表示与扰动的预测数据相比的改进，则修改该模型。
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公开(公告)号：US20180363478A1
公开(公告)日：2018-12-20
申请号：US15623842
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joshua Lee MARGOLIES , Victor John MORGAN , Matthew Troy HAFNER
CPC classification number: F01D5/288 , F01D9/02 , F01D9/023 , F01D25/005 , F01D25/007 , F01D25/24 , F05D2240/11 , F05D2240/122 , F05D2240/304 , F05D2240/35 , F05D2240/80 , F05D2250/292 , F05D2300/175 , F05D2300/6033 , F05D2300/611 , F23R3/002 , F23R3/007
Abstract: A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate comprising a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.
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10.发明申请公开(公告)号：US20180355725A1
公开(公告)日：2018-12-13
申请号：US15621394
申请日：2017-06-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor John MORGAN , Andres Jose GARCIA-CRESPO , Elisabeth Kraus BLACK , George Andrew GERGELY , Jonathan Glenn REED
IPC: F01D5/08
CPC classification number: F01D5/085 , B22F3/1055 , B22F5/009 , B23K1/0018 , B23K26/342 , B23K31/02 , B23K2101/001 , B23K2103/26 , B33Y10/00 , B33Y80/00 , F01D5/147 , F01D5/186 , F01D5/187 , F01D9/023 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2230/22 , F05D2230/31 , F05D2230/51 , F05D2240/11 , F05D2240/81 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R2900/00018 , F23R2900/03044
Abstract: A method of creating a cooling arrangement for a turbine component, and a cooling arrangement are provided. The turbine component includes an interior cooling passage formed therein. The method comprises a step of forming a slot through a sidewall of the turbine component. The method further comprises a step of forming an insert having one or more cooling features and a cavity. The method further comprises a step of positioning the insert within the slot. The method further comprises a step of securing the insert within the slot. The method further comprises a step of forming at least one passage in fluid communication with the internal cooling passage, the insert, and an exterior surface of the turbine component.
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