公开(公告)号：US10145000B2

公开(公告)日：2018-12-04

申请号：US15167201

申请日：2016-05-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Yan Cui ,  Srikanth Chandrudu Kottilingam ,  Sandip Dutta ,  Brian Lee Tollison

IPC: C23C4/134 ,  C23C4/129 ,  C23C4/06 ,  C23C24/04 ,  C23C4/12 ,  C23C4/18 ,  C23C4/073 ,  F01D5/28 ,  B22F3/11 ,  B22F5/00 ,  B22F5/04 ,  B22F7/08 ,  C23C28/00 ,  B22F3/24

Abstract: A thermally dissipative article and a method of forming a thermally dissipative article are disclosed. The thermally dissipative article includes a component, a porous material formed in a layer on the component. The method of forming a thermally dissipative article includes providing a metal powder mixture and a soluble particulate mixture which forms a porous coating upon sintering and immersion in a solvent to remove the soluble particulate.

公开(公告)号：US20180340427A1

公开(公告)日：2018-11-29

申请号：US15603785

申请日：2017-05-24

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Gary Michael Itzel

IPC: F01D5/18

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage extending between a root and a tip of the airfoil. The airfoil further defines a pocket positioned between the cooling passage and an exterior surface of the airfoil and spaced apart from the cooling passage and the exterior surface. The pocket provides a thermal impediment between the cooling passage and the exterior surface of the airfoil.

公开(公告)号：US10030537B2

公开(公告)日：2018-07-24

申请号：US14880565

申请日：2015-10-12

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Joseph Anthony Weber ,  Peter Galen Stevens

IPC: F01D25/12 ,  F02C7/12 ,  F02C3/04 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D9/041 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2260/204 ,  F05D2260/221 ,  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 outer flow boundaries of the turbine nozzle. The inner band includes a gas side surface that is at least partially covered by one or more inner plates. The inner band also includes a plurality of cooling channels formed within the gas side surface beneath the one or more inner plates. The outer band includes a gas side surface that is at least partially covered by one or more outer plates. The outer band comprises a plurality of cooling channels formed within the gas side surface beneath the one or more outer plates.

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

IPC: B22F3/105 ,  B33Y30/00 ,  B33Y50/02 ,  B23K26/342 ,  B23K26/70 ,  B23K15/00

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.

公开(公告)号：US09995151B2

公开(公告)日：2018-06-12

申请号：US14828094

申请日：2015-08-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ibrahim Sezer ,  Gary Michael Itzel ,  Jaime Javier Maldonado ,  Sandip Dutta

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C7/12 ,  F23R3/00

CPC classification number: F01D5/189 ,  F01D5/186 ,  F01D9/02 ,  F01D25/12 ,  F02C7/12 ,  F05D2250/32 ,  F05D2250/324 ,  F05D2260/201 ,  F05D2260/2212 ,  F23R3/002 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: An article is disclosed including a manifold, an article wall having at least one external aperture, and a post-impingement cavity disposed between the manifold and the article wall. The manifold includes an impingement plate defining a plenum having a plenum surface, and at least one impingement aperture. The at least one impingement aperture interfaces with the plenum at an intake aperture having a flow modification structure, which, together with the at least one impingement aperture, defines an exhaust aperture. The manifold exhausts a fluid from the plenum into the intake aperture, through the at least one impingement aperture, out the exhaust aperture, into the post-impingement cavity, and through the at least one external aperture.

公开(公告)号：US20180112538A1

公开(公告)日：2018-04-26

申请号：US15334585

申请日：2016-10-26

Applicant: General Electric Company

Inventor： David Wayne Weber ,  Sandip Dutta ,  Brendon James Leary

IPC: F01D5/18

Abstract: Various geometries for a trailing edge cooling system for a turbine blade is disclosed. The trailing edge cooling system may include a plurality of cooling circuits extending at least partially along a radial length of a trailing edge of the turbine blade. Each cooling circuit may include an outward leg extending axially toward the trailing edge, and a plurality of turn legs in fluid communication with the outward leg. The plurality of turn legs may be positioned adjacent the trailing edge. Each cooling circuit may also include a return leg positioned adjacent the outward leg and extending axially from the trailing edge. The return leg may include a first portion and a second portion. The first portion may have a first width, and a second may have a second width that is greater than the first width of the first portion.

公开(公告)号：US20180112537A1

公开(公告)日：2018-04-26

申请号：US15334563

申请日：2016-10-26

Applicant: General Electric Company

Inventor： David Wayne Weber ,  Sandip Dutta

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/026 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2260/202

Abstract: A trailing edge cooling system for a turbine blade is disclosed. The system may include a cooling circuit including an outward leg, and a return leg positioned adjacent the outward leg. The outward and return leg each may extend toward and away, respectively, from a trailing edge of the turbine blade. The cooling circuit may also include a plurality of turn legs. The plurality of turn legs may include a turn leg positioned directly adjacent the trailing edge of the turbine blade, and a distinct turn leg positioned axially adjacent the turn leg, and opposite the trailing edge of the turbine blade. The distinct turn leg may be oriented non-parallel to at least one of the outward leg and the return leg.

公开(公告)号：US20170101891A1

公开(公告)日：2017-04-13

申请号：US14880575

申请日：2015-10-12

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Gary Michael Itzel ,  Stephen Paul Wassynger

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 defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.