公开(公告)号：US20200049017A1

公开(公告)日：2020-02-13

申请号：US16656650

申请日：2019-10-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip DUTTA ,  James ZHANG ,  Gary Michael ITZEL ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02 ,  F01D5/28 ,  F01D5/14

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

公开(公告)号：US20170350259A1

公开(公告)日：2017-12-07

申请号：US15174182

申请日：2016-06-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip DUTTA ,  James ZHANG ,  Gary Michael ITZEL ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

IPC: F01D5/18 ,  B23K26/342 ,  B23K26/70 ,  B22F3/105 ,  B22F3/24 ,  B23K15/00 ,  B23K26/00 ,  F01D25/12 ,  C23C28/04 ,  F01D9/02 ,  B33Y80/00 ,  B33Y10/00 ,  B23K103/08 ,  B23K101/00

CPC classification number: F01D5/187 ,  B22F3/1055 ,  B22F3/24 ,  B22F2998/10 ,  B23K15/0086 ,  B23K15/0093 ,  B23K26/0006 ,  B23K26/342 ,  B23K26/70 ,  B23K2101/001 ,  B23K2103/08 ,  B33Y10/00 ,  B33Y80/00 ,  C23C28/042 ,  F01D5/147 ,  F01D5/282 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/30 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2260/20 ,  F05D2260/204 ,  F05D2300/175 ,  F05D2300/6033

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

公开(公告)号：US20170350256A1

公开(公告)日：2017-12-07

申请号：US15174332

申请日：2016-06-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip DUTTA ,  James ZHANG ,  Gary Michael ITZEL ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

IPC: F01D5/18 ,  F01D5/28 ,  F01D25/12 ,  F01D9/04 ,  F01D25/00

CPC classification number: F01D5/186 ,  F01D5/147 ,  F01D5/187 ,  F01D5/282 ,  F01D9/041 ,  F01D25/005 ,  F01D25/12 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/204 ,  F05D2300/175 ,  F05D2300/6033

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

公开(公告)号：US20170276000A1

公开(公告)日：2017-09-28

申请号：US15079346

申请日：2016-03-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary John SNIDER ,  John McConnell DELVAUX ,  Glenn Curtis TAXACHER

IPC: F01D9/02 ,  F01D11/00

CPC classification number: F01D9/02 ,  F01D11/005 ,  F01D11/10 ,  F01D25/246 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2300/6033 ,  F05D2300/614

Abstract: An apparatus is disclosed including a first article, a second article, and a third article disposed adjacent to one another, with the first article and the second article disposed between the third article and a gas path. The first article includes at least one first ceramic matrix composite ply defining a first cooperating feature. The second article includes at least one second ceramic matrix composite ply defining a second cooperating feature. The first cooperating feature and the second cooperating feature define a restricted flow path from the gas path to the third article, which includes a reduced volumetric flow rate of a gas from the gas path to the third article relative to a non-restricted flow path of a non-cooperating interface. A method for forming the apparatus includes forming and aligning the first cooperating feature and the second cooperating feature.

公开(公告)号：US20160376893A1

公开(公告)日：2016-12-29

申请号：US14752186

申请日：2015-06-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Canan Uslu HARDWICKE ,  John McConnell DELVAUX ,  Jason Robert PAROLINI ,  Matthew Troy HAFNER

IPC: F01D5/14 ,  B29C65/02 ,  B29C65/00

CPC classification number: F01D5/14 ,  B23P6/005 ,  B28B1/002 ,  B29C65/002 ,  B29C65/02 ,  B29C73/04 ,  B29L2031/7504 ,  C04B37/005 ,  C04B2235/5252 ,  C04B2235/5268 ,  C04B2235/60 ,  C04B2235/606 ,  C04B2237/083 ,  C04B2237/086 ,  C04B2237/78 ,  C04B2237/84 ,  F01D5/005 ,  F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F01D5/288 ,  F01D9/02 ,  F01D25/246 ,  F01D25/30 ,  F02K1/82 ,  F02K1/822 ,  F02K1/827 ,  F05D2230/40 ,  F05D2230/60 ,  F05D2230/64 ,  F05D2260/36 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/6012 ,  F05D2300/6033 ,  F05D2300/6034 ,  F05D2300/701 ,  Y02T50/675

Abstract: A method for treating a field operated component is disclosed which includes providing the component including a ceramic matrix composite and removing a first portion of the component, forming a first exposed surface on the component. The method further includes providing a second portion including the composite, the second portion having a second exposed surface including a conformation adapted to mate with the first exposed surface. The second portion is positioned in association with the component so as to replace the first portion, and the second portion and the component are joined to form a treated component. Another method is disclosed wherein the component is a turbine component which further includes removing an environmental barrier coating from the component, arranging and conforming the first exposed surface and the second exposed surface to define a joint, and applying an environmental barrier coating to the treated component.

Abstract translation: 公开了一种用于处理场致动部件的方法，其包括提供包括陶瓷基体复合材料的部件并且去除部件的第一部分，从而在部件上形成第一暴露表面。 该方法还包括提供包括复合材料的第二部分，第二部分具有包括适于与第一暴露表面配合的构型的第二暴露表面。 第二部分与部件相关联地定位以便替换第一部分，并且第二部分和部件被连接以形成处理的部件。 公开了另一种方法，其中所述部件是涡轮机部件，其进一步包括从所述部件移除环境阻挡涂层，将所述第一暴露表面和所述第二暴露表面布置和配合以限定接头，以及将环境阻挡涂层施加到所述被处理部件 。

公开(公告)号：US20140234117A1

公开(公告)日：2014-08-21

申请号：US13685230

申请日：2012-11-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ronald Ralph CAIRO ,  Jason Robert PAROLINI ,  John McConnell DELVAUX

IPC: F01D5/14

CPC classification number: F01D5/14 ,  C04B35/117 ,  C04B35/185 ,  C04B35/565 ,  C04B35/803 ,  C04B35/806 ,  C04B35/83 ,  C04B37/026 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/963 ,  C04B2237/123 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/405 ,  C04B2237/592 ,  C04B2237/64 ,  C04B2237/66 ,  C04B2237/708 ,  C04B2237/76 ,  C04B2237/84 ,  F01D5/3084 ,  F01D5/3092 ,  F05D2300/6033 ,  F23R3/007 ,  F23R3/60 ,  F23R2900/00017 ,  Y10T29/49336

Abstract: An apparatus to reduce wear and friction between CMC-to-metal attachment and interface, including a metal layer configured for insertion between a surface interface between a CMC component and a metal component. The surface interface of the metal layer is compliant relative to asperities of the surface interface of the CMC component. A coefficient of friction between the surface interface of the CMC component and the metal component is about 1.0 or less at an operating temperature between about 300° C. to about 325° C. and a limiting temperature of the metal component.

Abstract translation: 一种降低CMC与金属附件和界面之间的磨损和摩擦的装置，包括配置成插入在CMC组件和金属部件之间的表面界面之间的金属层。 金属层的表面界面相对于CMC部件的表面界面的粗糙度是顺从的。 在约300℃至约325℃的操作温度和金属组分的极限温度之间，CMC组分的表面界面与金属组分之间的摩擦系数约为1.0或更小。

公开(公告)号：US20140154073A1

公开(公告)日：2014-06-05

申请号：US13693350

申请日：2012-12-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ronald Ralph CAIRO ,  Jason Robert PAROLINI ,  John McConnell DELVAUX

IPC: F01D5/30

CPC classification number: F01D5/282 ,  F01D5/02 ,  F01D5/147 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3084 ,  F01D5/3092 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2300/6033 ,  Y02T50/672

Abstract: An apparatus having reduced wear and friction between CMC-to-metal attachment and interface of the apparatus, including a CMC component having a surface. The CMC component surface is configured for sliding contact with a surface of a metal component, the sliding contact resulting in formation of debris along the contacting surfaces. The surface of the CMC component has an engineered surface feature formed therein to substantially prevent an accumulation of debris along the contacting surfaces.

Abstract translation: 一种具有降低CMC与金属附件和设备界面之间的磨损和摩擦的装置，包括具有表面的CMC组件。 CMC部件表面构造成与金属部件的表面滑动接触，滑动接触导致沿着接触表面形成碎屑。 CMC组件的表面具有形成在其中的工程化表面特征，以基本上防止沿着接触表面积聚碎屑。

公开(公告)号：US20140093381A1

公开(公告)日：2014-04-03

申请号：US13633928

申请日：2012-10-03

Applicant: GENERAL ELECTRIC COMPANY

Inventor： John McConnell DELVAUX ,  Ronald Ralph CAIRO ,  Jason Robert PAROLINI

IPC: F01D5/14 ,  B23P15/04

CPC classification number: F01D5/282 ,  F01D5/288 ,  F05D2220/30 ,  F05D2260/941 ,  F05D2300/2261 ,  F05D2300/6012 ,  F05D2300/6033 ,  Y10T29/49336

Abstract: A turbine component, a turbine blade, and a turbine component fabrication process are disclosed. The turbine component includes ceramic matrix composite plies and a feature configured for preventing interlaminar tension of the ceramic matrix composite plies. The feature is selected from the group consisting of ceramic matrix composite tows or precast insert tows extending through at least a portion of the ceramic matrix composite plies, a woven fabric having fiber tows or a precast insert preventing contact between a first set of the ceramic matrix composite plies and a second set of the ceramic matrix composite plies, and combinations thereof. The process includes laying up ceramic matrix composite plies in a preselected arrangement and securing a feature configured for interlaminar tension.

Abstract translation: 公开了涡轮机部件，涡轮机叶片和涡轮部件制造工艺。 涡轮机部件包括陶瓷基体复合层和被配置为防止陶瓷基复合层的层间张力的特征。 该特征选自由陶瓷基质复合丝束或延伸穿过至少一部分陶瓷基复合层的预制插入丝束组成的组，具有纤维丝束的机织织物或防止第一组陶瓷基体之间接触的预制插入物 复合层和第二组陶瓷基复合层，及其组合。 该方法包括以预先布置的方式铺设陶瓷基质复合层，并确保构造用于层间张力的特征。