公开(公告)号：US10309252B2

公开(公告)日：2019-06-04

申请号：US14971478

申请日：2015-12-16

Applicant: General Electric Company

Inventor： Marc Lionel Benjamin ,  Benjamin Paul Lacy ,  Dipankar Pal ,  San Jason Nguyen

IPC: F01D25/12 ,  F01D9/00 ,  F02C3/04 ,  F01D9/04 ,  F01D11/08 ,  F01D25/24

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 at least one channel disposed within the body, wherein the at least one channel includes a first portion extending from upstream of the trailing edge towards the trailing edge in a first direction from the leading edge to the trailing edge, a second portion extending from the trailing edge to upstream of the trailing edge in a second direction from the trailing edge to the leading edge, and a third portion extending from upstream of the trailing edge towards the trailing edge in the first direction.

公开(公告)号：US10253986B2

公开(公告)日：2019-04-09

申请号：US14847347

申请日：2015-09-08

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D25/12 ,  F01D5/18 ,  F23R3/06 ,  B22F3/105 ,  B22F5/00 ,  B33Y10/00 ,  B33Y80/00 ,  B22F5/04 ,  B22F5/10

Abstract: A cooling article and method of forming a cooling article are provided. The cooling 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 cooling feature extending away from an outer surface of the body portion. The cooling feature disturbs fluid flow in the outer region. The method of forming a cooling article includes forming a body portion defining an inner region and an outer region, forming an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region, and forming a cooling feature extending away from an outer surface of the body portion. The cooling article is arranged and disposed for insertion within a hot gas path component of a turbine engine.

公开(公告)号：US20180347372A1

公开(公告)日：2018-12-06

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: F01D5/18 ,  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：US10087776B2

公开(公告)日：2018-10-02

申请号：US14847445

申请日：2015-09-08

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Srikanth Chandrudu Kottilingam ,  David Edward Schick

IPC: F01D25/12 ,  F01D5/18 ,  B23K26/354 ,  B23K26/342 ,  B22F5/04

Abstract: A cooling article and method of forming a cooling article are provided. The cooling 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 and the outer region, and a reinforcing feature extending at least partially along the body portion, the reinforcing feature being oriented with respect to a build direction. The method includes forming a body portion defining an inner region and an outer region, forming at least one reinforcing feature concurrently with the forming of the body portion, the at least one reinforcing feature extending at least partially along the body portion, and forming an aperture in the body portion, the aperture fluidly connecting the inner region to the outer region. The forming the body portion, forming the aperture, and forming the at least one reinforcing feature comprises additive manufacturing.

公开(公告)号：US20180149028A1

公开(公告)日：2018-05-31

申请号：US15364710

申请日：2016-11-30

Applicant: General Electric Company

Inventor： Sandip Dutta ,  Benjamin Paul Lacy ,  Gary Michael Itzel ,  Zachary John Snider

IPC: F01D9/06 ,  F01D5/18 ,  F01D25/14

CPC classification number: F01D9/065 ,  F01D5/189 ,  F01D11/08 ,  F01D25/14 ,  F05D2220/30 ,  F05D2260/201 ,  F05D2260/22141 ,  F05D2260/30

Abstract: The present disclosure is directed to a gas turbine engine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.

公开(公告)号：US09909432B2

公开(公告)日：2018-03-06

申请号：US14090832

申请日：2013-11-26

Applicant: General Electric Company

Inventor： Srikanth Chandrudu Kottilingam ,  Benjamin Paul Lacy ,  Brian Lee Tollison ,  David Edward Schick

IPC: F01D25/14 ,  F01D9/02 ,  B22F7/08 ,  F01D25/12 ,  F23R3/60 ,  B22F5/10 ,  C22C1/04 ,  C22C19/05

CPC classification number: F01D9/023 ,  B22F5/10 ,  B22F7/08 ,  C22C1/0433 ,  C22C19/056 ,  C22C19/057 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2260/201 ,  F23R3/60 ,  F23R2900/00018 ,  Y02T50/671 ,  Y02T50/676

Abstract: Aft frame assemblies for a gas turbine transition pieces include a body comprising an exterior surface and a plurality of interior surfaces, one or more exterior cooling holes disposed on the exterior surface of the body for capturing compressor discharge air outside of the transition piece, and a supplemental component bonded to at least one of the plurality of interior surfaces of the body. At least one cooling channel is at least partially defined by the supplemental component and the interior surface that the supplemental component is bonded to, wherein the at least one cooling channel fluidly connects at least one of the one or more exterior cooling holes to one or more interior cooling outlets that discharge the compressor discharge air captured from the at least one of the one or more exterior cooling holes.

公开(公告)号：US20170175580A1

公开(公告)日：2017-06-22

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 ,  F04D29/58 ,  F01D25/24 ,  F04D29/52 ,  F02C3/04 ,  F02C7/12

CPC classification number: F01D25/14 ,  F01D9/04 ,  F01D11/08 ,  F01D25/24 ,  F01D25/246 ,  F02C3/04 ,  F02C7/12 ,  F02C7/18 ,  F04D29/522 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2250/75 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

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：US20170101890A1

公开(公告)日：2017-04-13

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 ,  F02C3/04 ,  F02C7/12 ,  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：US09416662B2

公开(公告)日：2016-08-16

申请号：US14016769

申请日：2013-09-03

Applicant: General Electric Company

Inventor： Victor John Morgan ,  Benjamin Paul Lacy

IPC: F01D5/18 ,  F02C7/12 ,  F01D25/12 ,  F01D5/08

CPC classification number: F01D5/081 ,  F01D5/183 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/81 ,  F05D2260/202 ,  F05D2260/204 ,  Y10T29/4932

Abstract: A system for providing cooling for a turbine component that includes an outer surface exposed to combustion gases is provided. A component base includes at least one fluid supply passage coupleable to a source of cooling fluid. At least one feed passage communicates with the at least one fluid supply passage. At least one delivery channel communicates with the at least one feed passage. At least one cover layer covers the at least one feed passage and the at least one delivery channel, defining at least in part the component outer surface. At least one discharge passage extends to the outer surface. A diffuser section is defined in at least one of the at least one delivery channel and the at least one discharge passage, such that a fluid channeled through the system is diffused prior to discharge adjacent the outer surface.

Abstract translation: 提供了一种用于为包括暴露于燃烧气体的外表面的涡轮机部件提供冷却的系统。 组件底座包括至少一个可连接到冷却流体源的流体供给通道。 至少一个进料通道与至少一个流体供应通道连通。 至少一个输送通道与至少一个进料通道连通。 至少一个覆盖层覆盖至少一个进料通道和至少一部分外部表面的至少一个输送通道。 至少一个排出通道延伸到外表面。 扩散器部分限定在至少一个输送通道和至少一个排放通道中的至少一个中，使得通过系统引导的流体在邻近外表面排放之前扩散。

公开(公告)号：US09394796B2

公开(公告)日：2016-07-19

申请号：US13940806

申请日：2013-07-12

Applicant: General Electric Company

Inventor： Benjamin Paul Lacy ,  Brian Gene Brzek ,  Srikanth Chandrudu Kottilingam ,  David Edward Schick

IPC: F01D5/18 ,  B23P15/04 ,  F01D25/14 ,  F01D5/28

CPC classification number: F01D5/186 ,  B23P15/04 ,  B23P2700/06 ,  F01D5/288 ,  F01D25/145 ,  F05D2260/202 ,  Y10T29/49337

Abstract: A turbine component is provided. The turbine component includes an airfoil having a first surface and a second surface. A thermal barrier coating is coupled to the second surface, wherein the thermal barrier coating includes a first portion, a second portion and a trench defined between the first and second portions. A channel is coupled in flow communication to the first surface and the trench, wherein the channel includes a first sidewall and a second sidewall opposite of the first sidewall. The first and second sidewalls extend from the first surface and toward the trench at an angle. The turbine component includes a cover coupled to the second surface, wherein the cover includes a first end coupled to the first portion and a second end extending into the trench and spaced from the second portion.

Abstract translation: 提供涡轮机部件。 涡轮机部件包括具有第一表面和第二表面的翼型件。 热障涂层耦合到第二表面，其中热障涂层包括限定在第一和第二部分之间的第一部分，第二部分和沟槽。 通道以与第一表面和沟槽流动连通的方式耦合，其中该通道包括第一侧壁和与第一侧壁相对的第二侧壁。 第一和第二侧壁以一定角度从第一表面延伸到沟槽。 涡轮机部件包括联接到第二表面的盖，其中盖包括联接到第一部分的第一端和延伸到沟槽中并与第二部分间隔开的第二端。