公开(公告)号：US20140170433A1

公开(公告)日：2014-06-19

申请号：US13719772

申请日：2012-12-19

Applicant: GENERAL ELECTRIC COMPANY

Inventor： David Edward Schick ,  Srikanth Chandrudu Kottilingam ,  Benjamin Paul Lacy ,  John Wesley Harris, JR.

IPC: B22F7/08

CPC classification number: B22F7/08 ,  B22F5/009 ,  B22F5/04 ,  B22F5/10 ,  B23P2700/06 ,  C22C1/0433 ,  F01D5/187 ,  F05D2230/22 ,  F05D2260/204 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T428/12028 ,  Y10T428/24744

Abstract: Methods for providing a near-surface cooling microchannel in a component include forming a near-surface cooling microchannel in a first surface of a pre-sintered preform, disposing the first surface of the pre-sintered preform onto an outer surface of the base article such that an opening of the outer surface of the base article is aligned with the near-surface cooling microchannel in the first surface of the pre-sintered preform, and, heating the pre-sintered preform to bond it to the base article, wherein the opening of the outer surface of the base article remains aligned with the near-surface cooling microchannel in the first surface of the pre-sintered preform.

Abstract translation: 在组件中提供近表面冷却微通道的方法包括在预烧结预型件的第一表面中形成近表面冷却微通道，将预烧结预制件的第一表面设置在基底制品的外表面上， 基底制品的外表面的开口与预烧结预型件的第一表面中的近表面冷却微通道对准，并且加热预烧结的预成型件以将其粘合到基底制品上，其中开口 基底制品的外表面与预烧结预制件的第一表面中的近表面冷却微通道保持一致。

公开(公告)号：US10760430B2

公开(公告)日：2020-09-01

申请号：US15609598

申请日：2017-05-31

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Brian Peter Arness ,  Victor John Morgan ,  Stephen William Tesh

IPC: F01D5/08 ,  F01D5/18 ,  F01D9/04 ,  F01D9/06

Abstract: A hot gas path (HGP) component of an industrial machine includes primary and secondary cooling pathways. A body includes an internal cooling circuit carrying a cooling medium. A primary cooling pathway is spaced internally in the body and carries a primary flow of a cooling medium from an internal cooling circuit. A secondary cooling pathway is in the body and in fluid communication with an internal cooling circuit. The secondary cooling pathway is fluidly incommunicative and spaced internally from the primary cooling pathway. In response to an overheating event occurring, the secondary cooling pathway opens to allow a secondary flow of cooling medium through to the outer surface of the body and/or the primary cooling pathway. The primary flow flows in the primary cooling pathway prior to the overheating event, and the secondary flow of cooling medium does not flow until after an opening of the secondary cooling pathway.

公开(公告)号：US10655477B2

公开(公告)日：2020-05-19

申请号：US15219804

申请日：2016-07-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Gary Michael Itzel ,  Joseph Anthony Weber ,  David Edward Schick

IPC: F01D5/18 ,  B22F5/04 ,  B33Y80/00 ,  F01D9/04 ,  F01D25/12 ,  B22F3/105

Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.

公开(公告)号：US20200025026A1

公开(公告)日：2020-01-23

申请号：US16040062

申请日：2018-07-19

Applicant: General Electric Company

Inventor： Travis J Packer ,  Benjamin Paul Lacy ,  Ibrahim Sezer ,  Zachary John Snider ,  Brad Wilson VanTassel

IPC: F01D25/12 ,  F01D11/08

Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.

公开(公告)号：US20190390568A1

公开(公告)日：2019-12-26

申请号：US16015268

申请日：2018-06-22

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy

IPC: F01D25/12

Abstract: A cooled structure has a leading edge, a trailing edge, a first side portion orthogonal to each of the leading and trailing edge, and a second side portion opposite the first side portion and substantially orthogonal to each of the leading and trailing edge. The cooled structure includes a substrate surface defined by boundaries including the leading edge, trailing edge, first side and second side portion. A first set of cooling channels beneath the substrate surface extends from a first set of inlets proximate to the first side portion to a first set of exits proximate to the second side portion. A second set of cooling channels beneath the substrate surface extends from a second set of inlets proximate to the second side portion to a second set of exits proximate to the first side portion. Each first inlet overlaps with an exit of the second set of exits.

公开(公告)号：US10337343B2

公开(公告)日：2019-07-02

申请号：US14825553

申请日：2015-08-13

Applicant: General Electric Company

Inventor： Carlos Miguel Miranda ,  Benjamin Paul Lacy ,  Slawomir Rubinsztajn

IPC: F01D5/18 ,  F01D9/06 ,  F01D17/08 ,  F01D25/12 ,  F02C7/12

Abstract: A system according to various embodiments includes: a cooling network within a turbine component, the cooling network including at least one passageway fluidly connected with a surface of the turbine component; a cooling fluid source for providing a cooling fluid to the cooling network; and a temperature-actuated flow modulating device fluidly connected with the cooling fluid source and the cooling network, the temperature-actuated flow modulating device configured to: detect an ambient air temperature proximate the turbine component; and control a flow of the cooling fluid to the cooling network based upon the detected ambient air temperature.

公开(公告)号：US10221719B2

公开(公告)日：2019-03-05

申请号：US14971383

申请日：2015-12-16

Applicant: General Electric Company

Inventor： Marc Lionel Benjamin ,  Benjamin Paul Lacy ,  Gregory Thomas Foster ,  San Jason Nguyen

IPC: F01D25/14 ,  F02C7/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/24 ,  F02C3/04 ,  F02C7/12 ,  F04D29/52 ,  F04D29/58

Abstract: A shroud segment that includes a body including a leading edge, a trailing edge, a first side edge, a second side, and a pair of opposed lateral sides. A first lateral side is configured to interface with a cavity having a cooling fluid, and a second lateral side is oriented toward a hot gas flow path. The shroud segment includes a first channel disposed within the body having a first end portion and a second end portion and a second channel disposed within the body having a third end portion and a fourth end portion. The first and second channels are configured to receive the cooling fluid from the cavity to cool the body. The first end portion and the fourth end portion each include a hook-shaped portion having a free end.

公开(公告)号：US10184343B2

公开(公告)日：2019-01-22

申请号：US15016498

申请日：2016-02-05

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  David Edward Schick ,  Sandip Dutta

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

Abstract: A system having an impingement sleeve configured to receive a cooling flow is provided. The impingement sleeve includes a column of ports extending from an outer surface of the impingement sleeve, wherein each port of the column of ports is configured to direct an impingement stream toward a heated structure, and each impingement stream includes a portion of the cooling flow. Further, one or more pins are disposed outside the outer surface relative to the cooling flow, wherein each pin of the one or more pins is coupled between pairs of ports of the column of ports.

公开(公告)号：US10100666B2

公开(公告)日：2018-10-16

申请号：US13853556

申请日：2013-03-29

Applicant: General Electric Company

Inventor： Brian Gene Brzek ,  Victor John Morgan ,  Benjamin Paul Lacy

IPC: F01D25/12 ,  F01D5/14 ,  F01D9/02 ,  F01D5/18 ,  F01D9/04

Abstract: A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.

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.