公开(公告)号：US20180355730A1

公开(公告)日：2018-12-13

申请号：US15619600

申请日：2017-06-12

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Joseph Anthony Weber

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/14 ,  F01D5/18 ,  F05D2240/24 ,  F05D2260/20

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a passage extending from a root to a tip of the airfoil. The passage includes a first passage portion and a second passage portion. The first passage portion has a greater diameter than the second passage portion. The rotor blade also includes a first tube positioned within the first passage portion. The first tube is spaced apart from the airfoil. The rotor blade further includes a second tube positioned within the first passage portion. The second tube is positioned between the airfoil and the first tube. Furthermore, the rotor blade includes a plurality of inserts positioned within the first passage portion. The plurality of inserts is positioned between and in contact with the first and second tubes.

公开(公告)号：US09976441B2

公开(公告)日：2018-05-22

申请号：US14725374

申请日：2015-05-29

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Benjamin Paul Lacy ,  Gary Michael Itzel ,  Srikanth Chandrudu Kottilingam ,  Sandip Dutta ,  David Edward Schick

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02 ,  B33Y10/00 ,  B33Y80/00

CPC classification number: F01D25/12 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/189 ,  F01D9/02 ,  F05D2230/31 ,  F05D2260/201

Abstract: An article and method of forming an article are provided. The article includes a body portion separating an inner region and an outer region, an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and a conduit extending from an outer surface of the body portion at the aperture and being arranged and disposed to controllably direct fluid from the inner region to the outer region. The method includes providing a body portion separating an inner region and an outer region, providing an aperture in the body portion, and forming a conduit over the aperture, the conduit extending from an outer surface of the body portion and being arranged and disposed to controllably direct fluid from the inner region to the outer region. The article is arranged and disposed for insertion within a hot gas path component.

公开(公告)号：US20170175577A1

公开(公告)日：2017-06-22

申请号：US14974460

申请日：2015-12-18

Applicant: General Electric Company

Inventor： Sandip Dutta

IPC: F01D25/12 ,  F01D9/02 ,  F02C3/04

CPC classification number: F01D25/12 ,  F01D9/02 ,  F01D9/065 ,  F05D2250/21 ,  F05D2250/232 ,  F05D2260/201 ,  F05D2260/22141

Abstract: A nozzle for a turbine is disclosed. The nozzle includes a shell, an orifice plate disposed adjacent to the shell, an impingement chamber formed between the shell and the orifice plate, and at least one baffle extending from the orifice plate into the impingement chamber to push a flow of cooling fluid into the shell.

公开(公告)号：US20170101892A1

公开(公告)日：2017-04-13

申请号：US14880580

申请日：2015-10-12

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Gary Michael Itzel ,  James William Vehr

IPC: F01D25/12 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band define a first set of cooling channels and a second set of cooling channels formed beneath a gas side surface of the corresponding inner band or outer band. The inner band or the outer band further define a coolant distribution plenum that is in fluid communication with the first and second sets of cooling channels. The coolant distribution plenum provides a stream of coolant to at least one of the first set of cooling channels and the second set of cooling channels.

公开(公告)号：US11826830B2

公开(公告)日：2023-11-28

申请号：US16916722

申请日：2020-06-30

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip Dutta ,  Zachary Snider ,  Srikanth Chandrudu Kottilingam ,  Stephen Wassynger ,  Joseph Moroso

IPC: F01D9/04 ,  B22F5/04 ,  F01D25/12 ,  B22F7/08 ,  F01D5/14 ,  B22F10/28 ,  F04D29/66

CPC classification number: B22F5/04 ,  B22F7/08 ,  F01D5/147 ,  F01D9/041 ,  F01D9/044 ,  F01D25/12 ,  B22F10/28 ,  F04D29/666 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  F05D2230/50 ,  F05D2240/128 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2260/202 ,  Y02P10/25

Abstract: At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.

公开(公告)号：US11333024B2

公开(公告)日：2022-05-17

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 ,  F01D5/14 ,  F01D5/28 ,  F01D9/02 ,  F01D25/12

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：US10731487B2

公开(公告)日：2020-08-04

申请号：US15437005

申请日：2017-02-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip Dutta ,  Zachary Snider ,  Srikanth Chandrudu Kottilingam ,  Stephen Wassynger ,  Joseph Moroso

IPC: F01D9/04 ,  F01D25/12 ,  B22F5/04 ,  B22F3/105 ,  B22F7/08 ,  F01D5/14

Abstract: At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a mounting location of the turbine component in a turbine. Methods of manufacturing articles and turbine components are also disclosed.

公开(公告)号：US10563294B2

公开(公告)日：2020-02-18

申请号：US15451914

申请日：2017-03-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip Dutta ,  Srikanth Chandrudu Kottilingam

IPC: C23C4/18 ,  B33Y80/00 ,  C23C4/11 ,  F01D25/12 ,  B33Y10/00 ,  B22F5/04 ,  B22F5/00 ,  B22F3/105

Abstract: A method of fabricating a component having active cooling with film holes and other exposed holes is provided. The method includes the step of providing a component including at least one aperture disposed on a surface of the component and fluidly connected to at least one fluid flow passage, the at least one aperture comprising a floor extending from the at least one fluid flow passage to the surface of the component, and a ceiling facing the floor. The method further includes the step of applying a thermal barrier coating over at least a portion of a substrate. The method further includes the step of removing a portion of the thermal barrier coating covering the at least one aperture. The method further includes the step of forming with an additive manufacturing method one or both of a sharp-edged hood of the at least one aperture and at least one feature disposed on the floor.

公开(公告)号：US10472973B2

公开(公告)日：2019-11-12

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 ,  F01D5/14 ,  F01D5/28

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：US10309228B2

公开(公告)日：2019-06-04

申请号：US15177370

申请日：2016-06-09

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Kassy Moy Hart

IPC: F01D5/18 ,  F01D9/06 ,  F01D11/24

Abstract: The present disclosure is directed to an impingement insert for a gas turbine engine. The impingement insert includes an insert wall having an inner surface and an outer surface spaced apart from the inner surface. A nozzle extends outwardly from the outer surface of the insert wall. The nozzle includes an outer surface and a circumferential surface. The insert wall and the nozzle collectively define a cooling passage extending from the inner surface of the insert wall to the outer surface of the nozzle. The cooling passage includes an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion. The cooling passage further includes a cross-sectional shape having a semicircular portion and a non-circular portion.