公开(公告)号：US20170173672A1

公开(公告)日：2017-06-22

申请号：US14977028

申请日：2015-12-21

Applicant: General Electric Company

Inventor： Gregory Thomas Foster ,  David Wayne Weber ,  Michelle Jessica Iduate ,  Brendon James Leary ,  Joseph Anthony Weber

IPC: B22C9/10 ,  B22C9/24 ,  G01B17/02 ,  F01D5/18

CPC classification number: B22C9/103 ,  B22C9/108 ,  B22C9/12 ,  B22C9/24 ,  B22C21/14 ,  F01D5/187 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2260/20 ,  G01B17/02 ,  G01B21/08

Abstract: A core for a turbine airfoil casting according to an embodiment includes: a center plenum section; and a plurality of outer passage sections; wherein the center plenum section includes at least one boss extending outwardly from the center plenum to an outer profile of the core.

公开(公告)号：US09416675B2

公开(公告)日：2016-08-16

申请号：US14164707

申请日：2014-01-27

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  Christopher Donald Porter ,  David Edward Schick ,  David Wayne Weber

IPC: F01D11/00 ,  F16J15/06 ,  F16J15/02 ,  F01D9/02 ,  F16J15/12

CPC classification number: F01D11/005 ,  F01D9/023 ,  F01D11/003 ,  F05D2240/11 ,  F05D2240/55 ,  F16J15/02 ,  F16J15/061 ,  F16J15/126

Abstract: Sealing device for providing seals between adjacent components, and turbomachines utilizing such sealing devices, are provided. A sealing device includes a seal plate insertable between the adjacent components, the seal plate comprising a first face and an opposing second face. The sealing device further includes a plurality of pins extending from one of the first face or the second face, the plurality of pins configured to space the one of the first face or the second face from contact surfaces of the adjacent components.

Abstract translation: 提供了用于在相邻部件之间提供密封的密封装置，以及利用这种密封装置的涡轮机。 密封装置包括可插入相邻部件之间的密封板，密封板包括第一面和相对的第二面。 所述密封装置还包括从所述第一面或所述第二面中的一个延伸的多个销，所述多个销用于将所述第一面或所述第二面中的一个从所述相邻部件的接触表面间隔开。

公开(公告)号：US20150218962A1

公开(公告)日：2015-08-06

申请号：US14173949

申请日：2014-02-06

Applicant: General Electric Company

Inventor： David Wayne Weber ,  Gregory Thomas Foster ,  Benjamin Paul Lacy ,  Aaron Ezekiel Smith ,  Dustin Michael Earnhardt

IPC: F01D25/12 ,  B22C7/02 ,  B22C9/10 ,  B22C9/24 ,  B22C9/04

CPC classification number: B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/103 ,  B22C9/108 ,  B22C9/24 ,  F01D5/186 ,  F05D2230/211 ,  F05D2240/81 ,  F05D2260/204

Abstract: A core for forming micro channels within a turbine component is provided. The core includes a base comprising a first side and a second side; and a core assembly coupled to the second side. The core assembly further includes a plurality of channel members, wherein each channel member has a first end, a second end, and a channel body coupled to and extending between said first end and said second end. The channel body includes a channel shape configured to form the micro channels within the turbine component.

Abstract translation: 提供了一种用于在涡轮机部件内形成微通道的芯。 芯部包括一个包括第一面和第二面的基底; 以及耦合到第二侧的芯组件。 芯组件还包括多个通道构件，其中每个通道构件具有第一端，第二端和与所述第一端和所述第二端连接并在其之间延伸的通道体。 通道体包括被配置为在涡轮部件内形成微通道的通道形状。

公开(公告)号：US20140341724A1

公开(公告)日：2014-11-20

申请号：US13893508

申请日：2013-05-14

Applicant: GENERAL ELECTRIC COMPANY

Inventor： David Wayne Weber ,  Dustin Michael Earnhardt ,  Michelle Jessica Rogers

IPC: B22C21/14 ,  F01D5/18 ,  F01D25/12

CPC classification number: B22C21/14 ,  B22C9/108 ,  F01D5/187 ,  F01D25/12 ,  F05D2230/21 ,  Y10T428/12361 ,  Y10T428/24273

Abstract: A core tie having a varying cross sectional diameter, a component including such a core tie, and a method of casting a hot gas path component for a turbomachine are provided herein. In an embodiment, the core tie includes a tie member having an axial length; and a cross sectional diameter which varies along the axial length of the tie member. A variation in the cross sectional diameter of the tie member positively secures a position of the core tie relative to the core.

Abstract translation: 本文提供具有变化的横截面直径的芯带，包括这种芯带的部件，以及铸造用于涡轮机的热气体路径部件的方法。 在一个实施例中，芯线包括具有轴向长度的连接构件; 并且横截面直径沿着连接构件的轴向长度而变化。 连接件的横截面直径的变化正确地确保了芯连接件相对于芯部的位置。

公开(公告)号：US20140154062A1

公开(公告)日：2014-06-05

申请号：US13690485

申请日：2012-11-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： David Wayne Weber ,  Kevin Richard Kirtley ,  Victor John Morgan ,  Neelesh Nandkumar Sarawate

IPC: F02C7/28

CPC classification number: F02C7/28 ,  F01D11/00 ,  F01D11/005 ,  F01D11/006 ,  F05D2230/90 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2300/43 ,  F05D2300/611 ,  Y10T29/49229

Abstract: A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed.

Abstract translation: 用于放置在燃气涡轮机的两个涡轮机部件之间以密封部件之间的间隙的狭槽中的密封件可以包括密封元件，其尺寸设计成能够放置在槽内并且在燃气轮机的操作期间基本上密封间隙 。 牺牲涂层可以位于密封元件上。 牺牲涂层可以被配置成基本上符合狭缝尺寸的尺寸，牺牲涂层包括可通过加热将其从密封元件移除到燃气涡轮机运行期间达到的温度的材料。 还公开了相关的燃气轮机组件和组装方法。