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公开(公告)号：US10882158B2
公开(公告)日：2021-01-05
申请号：US16260768
申请日：2019-01-29
Applicant: General Electric Company
Inventor： Arthur S. Peck , Gabriel DellaFera , Paul Stephen Dimascio , Jon Conrad Schaeffer
Abstract: A method of treating a substrate of a turbomachine component includes applying a coating to a surface of the substrate of the turbomachine component and peening the substrate after applying the coating to the surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate. A method of treating an internal surface of a turbomachine component includes directing a peening force at the internal surface within a cooling passage of the turbomachine component.
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Patent Agency Ranking
12.发明授权公开(公告)号：US09926791B2
公开(公告)日：2018-03-27
申请号：US14959307
申请日：2015-12-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Ronald Ralph Cairo , Paul Stephen Dimascio , Jason Robert Parolini
CPC classification number: F01D5/282 , B29K2709/04 , F01D5/284 , F01D9/02 , F01D9/04 , F01D25/24 , F01D25/30 , F02K1/82 , F05D2300/6033 , Y10T428/1317
Abstract: A ceramic matrix composite article and a process of fabricating a ceramic matrix composite are disclosed. The ceramic matrix composite article includes a matrix distribution pattern formed by a manifold and ceramic matrix composite plies laid up on the matrix distribution pattern, includes the manifold, or a combination thereof. The manifold includes one or more matrix distribution channels operably connected to a delivery interface, the delivery interface configured for providing matrix material to one or more of the ceramic matrix composite plies. The process includes providing the manifold, forming the matrix distribution pattern by transporting the matrix material through the manifold, and contacting the ceramic matrix composite plies with the matrix material.
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13.发明申请公开(公告)号：US20160115799A1
公开(公告)日：2016-04-28
申请号：US14522824
申请日：2014-10-24
Applicant: General Electric Company
Inventor： Dechao Lin , Wei Chen , Xiaoxue Diao , Paul Stephen Dimascio , Srikanth Chandrudu Kottilingam , Brian Lee Tollison
CPC classification number: B23K9/16 , B23K9/0026 , B23K9/046 , B23K9/23 , B23K2101/001 , B23K2101/045 , F01D5/186 , F05D2230/232 , F05D2230/30 , F05D2240/127 , F05D2260/2212 , F23R3/002 , F23R3/005 , F23R2900/00018 , F23R2900/03045 , Y02T50/676
Abstract: A method of forming a plurality of turbulators on a turbomachine surface includes depositing a portion of material on the turbomachine surface forming a first portion of the plurality of turbulators, adding additional material to the first portion, and establishing a desired dimension of the plurality of turbulators.
Abstract translation: 在涡轮机表面上形成多个湍流器的方法包括将一部分材料沉积在涡轮机表面上，形成多个湍流器的第一部分，向第一部分添加额外的材料，以及建立多个湍流器的期望尺寸 。
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公开(公告)号：US20200238475A1
公开(公告)日：2020-07-30
申请号：US16260768
申请日：2019-01-29
Applicant: General Electric Company
Inventor： Arthur S. Peck , Gabriel DellaFera , Paul Stephen Dimascio , Jon Conrad Schaeffer
Abstract: A method of treating a substrate of a turbomachine component includes applying a coating to a surface of the substrate of the turbomachine component and peening the substrate after applying the coating to the surface by directing a peening force onto the coating whereby the peening force on the coating is transferred through the coating to the substrate. A method of treating an internal surface of a turbomachine component includes directing a peening force at the internal surface within a cooling passage of the turbomachine component.
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公开(公告)号：US09587632B2
公开(公告)日：2017-03-07
申请号：US13690298
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Stephen Dimascio , Michael Douglas Arnett , Rebecca Evelyn Hefner
CPC classification number: F03G7/06
Abstract: A thermally-controlled component and thermal control process are disclosed. The thermally-controlled component includes thermally-responsive features. The thermally-responsive features are configured to modify a flow path to control temperature variation of the thermally-controlled component. The thermally-responsive features deploy from or retract toward a surface of the thermally-controlled component in response to a predetermined temperature change. The thermal control process includes modifying the flow path in the thermally-controlled component to control temperature variation of the thermally-controlled component and/or cooling a region of the thermally-controlled component through the thermally-responsive features deploying from or retracting toward a surface of the thermally-controlled component.
Abstract translation: 公开了一种热控部件和热控制工艺。 热控制部件包括热响应特征。 热响应特征被配置为修改流路以控制热控部件的温度变化。 响应于预定的温度变化，热响应特征从热控部件的表面展开或缩回。 热控制过程包括修改热控部件中的流动路径以控制热控部件的温度变化和/或通过从表面向或朝向表面展开的热响应特征来冷却热控部件的区域 的热控部件。
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公开(公告)号：US20130287587A1
公开(公告)日：2013-10-31
申请号：US13906075
申请日：2013-05-30
Applicant: General Electric Company
Inventor： Mark L. Hunt , Paul Stephen Dimascio , Warren Martin Miglietti , Steve P. Byam , Matthew James O'Connell
IPC: F01D5/14
CPC classification number: F01D5/147 , B23P15/04 , F01D5/20 , F01D5/282 , Y10T29/49337 , Y10T29/49339
Abstract: A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice.
Abstract translation: 公开了一种复合涡轮叶片及其制造方法。 复合涡轮机叶片包括涡轮叶片部分，其包括第一材料和包括第二材料的第一顶板。 涡轮机叶片部分具有外壁和围绕中空内腔的内壁，以及从外壁延伸到限定流体连接到中空内腔的孔的内壁的顶表面。 第一顶板可以沿着顶表面附接到涡轮机叶片，并且从涡轮机叶片的外壁的近端延伸穿过孔口以覆盖孔口。
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