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41.发明申请MODIFIED TURBINE COMPONENTS WITH INTERNALLY COOLED SUPPLEMENTAL ELEMENTS AND METHODS FOR MAKING THE SAME 有权具有内部冷却补充元件的改型涡轮机组件及其制造方法公开(公告)号：US20150147164A1
公开(公告)日：2015-05-28
申请号：US14087381
申请日：2013-11-22
Applicant: General Electric Company
Inventor： Yan Cui , Ganjiang Feng , Srikanth Chandrudu Kottilingam , David Edward Schick , Cem Murat Eminoglu
CPC classification number: F01D5/188 , B23K2101/001 , B23P6/005 , F01D5/005 , F01D5/18 , F01D25/14 , F05D2230/237 , F05D2230/80 , F05D2240/121 , Y02T50/676 , Y10T29/49231
Abstract: Modified turbine components include an original turbine component comprising an outer wail enclosing an internal cavity, wherein the outer wall has an original portion removed therefrom to expose the internal cavity, and, an internally cooled supplemental element joined to the outer wall that replaces the original portion removed from the outer wall and re-encloses the internal cavity. The internally cooled supplemental element comprises one or more cooling channels that circulate air from the internal cavity through at least a portion of the internally cooled supplemental element.
Abstract translation: 改进的涡轮机部件包括原始涡轮机部件，其包括封闭内部空腔的外部壁部，其中外壁具有从其中移除的原始部分以暴露内部空腔，以及连接到外壁的内部冷却的补充元件，其代替原始部分 从外壁移除并重新封闭内腔。 内部冷却的辅助元件包括一个或多个冷却通道，其使来自内部空腔的空气通过内部冷却的补充元件的至少一部分循环。
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公开(公告)号：US20150064019A1
公开(公告)日：2015-03-05
申请号：US14014528
申请日：2013-08-30
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/186 , B22F3/1055 , B22F5/04 , B22F5/10 , B22F7/004 , F01D5/183 , F01D5/187 , F05D2300/514 , F05D2300/612 , Y02P10/295
Abstract: The present application provides a hot gas path component for use with a gas turbine engine. The hot gas path component may include an airfoil, an internal cooling cavity, and a porous section created by a direct metal laser melting technique. The porous section may be built into the airfoil or the airfoil may be built separately and attached to the airfoil.
Abstract translation: 本申请提供了一种与燃气涡轮发动机一起使用的热气路径部件。 热气体路径部件可以包括翼型件，内部冷却腔和通过直接金属激光熔化技术产生的多孔部分。 多孔部分可以内置在翼型件中，或者翼型件可以单独构建并附接到翼型件。
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公开(公告)号：US20140260327A1
公开(公告)日：2014-09-18
申请号：US13777019
申请日：2013-02-26
Applicant: General Electric Company
IPC: F02C3/04
CPC classification number: F01D5/18 , F01D9/02 , F01D11/001 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/23 , F05D2240/81 , F05D2300/17 , Y02T50/672 , Y02T50/676 , Y10T29/4932
Abstract: The present invention is an article containing internal cooling channels located near at least one surface. In an embodiment, the cooled article includes a base material, a first layer, and a second layer. Here, the first layer is bonded to the base material and the second layer is bonded to the first layer, wherein at least one closed cooling channel is disposed within a portion of the first layer and a portion of the second layer.
Abstract translation: 本发明是一种包含位于至少一个表面附近的内部冷却通道的物品。 在一个实施例中，冷却的制品包括基材，第一层和第二层。 这里，第一层结合到基材上，第二层与第一层接合，其中至少一个封闭的冷却通道设置在第一层的一部分和第二层的一部分内。
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公开(公告)号：US10731483B2
公开(公告)日：2020-08-04
申请号：US14962759
申请日：2015-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Srikanth Chandrudu Kottilingam , Jon Conrad Schaeffer , Brian Lee Tollison , Yan Cui , David Edward Schick
Abstract: A thermal management article is disclosed including a substrate and a first coating disposed on the substrate. The first coating includes a first coating surface and at least one passageway disposed between the substrate and the first coating surface. The at least one passageway defines at least one fluid pathway. A method for forming a thermal management article is disclosed including attaching at least one passageway to a substrate. The at least one passageway includes a passageway wall having a wall thickness and defines at least one fluid pathway. A first coating is applied to the substrate and the passageway wall, forming a first coating surface. The at least one passageway is disposed between the substrate and the first coating surface.
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公开(公告)号：US10655477B2
公开(公告)日：2020-05-19
申请号：US15219804
申请日：2016-07-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Joseph Anthony Weber , David Edward Schick
Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.
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Patent Agency Ranking
公开(公告)号：US10184343B2
公开(公告)日：2019-01-22
申请号：US15016498
申请日：2016-02-05
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , David Edward Schick , Sandip Dutta
Abstract: A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.
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公开(公告)号：US10029299B2
公开(公告)日：2018-07-24
申请号：US14794839
申请日：2015-07-09
Applicant: General Electric Company
Inventor： Yan Cui , Srikanth Chandrudu Kottilingam , David Edward Schick
IPC: B22C9/02 , B22C9/10 , B22C9/24 , B22C1/00 , B22C1/16 , B22D25/02 , B22C9/04 , B22D29/00 , B33Y10/00 , B33Y80/00
Abstract: The present application provides a method of producing a component. The method may include the steps of creating a dissolvable ceramic material mold in an additive manufacturing process, casting a metallic material in the dissolvable ceramic material mold, creating the component, and dissolving the dissolvable ceramic material. The component may be a turbine component.
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公开(公告)号：US20180200790A1
公开(公告)日：2018-07-19
申请号：US15405668
申请日：2017-01-13
Applicant: General Electric Company
Inventor： Kassy Moy Hart , Sandip Dutta , Srikanth Chandrudu Kottilingam , David Edward Schick
CPC classification number: B22F3/1055 , B22F2003/1056 , B23K26/703 , B23K2101/001 , B33Y30/00 , B33Y50/02 , Y02P10/295
Abstract: This disclosure provides systems and tooling for cooling components during additive manufacturing. A build plate supports layers of powdered materials as they are positioned and selectively fused to create the component. The build plate defines a build surface and the build surface retracts in a working direction opposite a build direction for the component. At least one vertical cooling structure is provided perpendicular to the build plate and protruding from the build plate as the build surface retracts. The vertical cooling structure cools at least a portion of the component through unfused powdered materials between the vertical cooling structure and the component.
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公开(公告)号：US20180119570A1
公开(公告)日：2018-05-03
申请号：US15342185
申请日：2016-11-03
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Christopher Donald Porter , David Edward Schick , Lyndsay Marie Kibler
CPC classification number: F01D25/12 , F01D5/187 , F01D11/08 , F02C3/04 , F05D2230/22 , F05D2230/50 , F05D2240/11 , F05D2240/128 , F05D2240/30 , F05D2240/81 , F05D2250/71 , F05D2260/204 , F05D2260/2214
Abstract: A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.
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公开(公告)号：US20170334188A1
公开(公告)日：2017-11-23
申请号：US15661126
申请日：2017-07-27
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Christopher Donald Porter , David Edward Schick
CPC classification number: B33Y80/00 , B22F3/1055 , B22F5/009 , B22F7/062 , B22F2999/00 , B33Y10/00 , F01D5/225 , F01D11/24 , F01D25/12 , F05D2230/31 , F05D2230/51 , F05D2240/11 , F05D2240/81 , F05D2260/202 , Y02P10/295 , B22F2203/05
Abstract: Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
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