公开(公告)号：US20170350260A1

公开(公告)日：2017-12-07

申请号：US15174271

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 ,  F01D9/02 ,  F01D25/12

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/282 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/30 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  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. 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：US20170328203A1

公开(公告)日：2017-11-16

申请号：US15150573

申请日：2016-05-10

Applicant: GENERAL ELECTRIC COMPANY

Inventor： James ZHANG ,  James Tyson BALKCUM, III ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

IPC: F01D1/04

CPC classification number: F01D1/04 ,  F01D11/001 ,  F01D11/008 ,  F05D2240/11 ,  F05D2240/55

Abstract: A turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a tip distal from the outer wall segment such that the tips form a seal with the inner wall segments at an inner flow path of the turbine. An inner wall assembly and a turbine assembly method are also disclosed.

公开(公告)号：US20200182067A1

公开(公告)日：2020-06-11

申请号：US16787819

申请日：2020-02-11

Applicant: GENERAL ELECTRIC COMPANY

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

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