公开(公告)号：US20220412219A1

公开(公告)日：2022-12-29

申请号：US17894414

申请日：2022-08-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Metodi Blagoev Zlatinov ,  Thomas Earl Dyson

IPC: F01D5/18

Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling; hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

公开(公告)号：US20220145764A1

公开(公告)日：2022-05-12

申请号：US17582305

申请日：2022-01-24

Applicant: General Electric Company

Inventor： Zachary Daniel Webster ,  Aaron Ezekiel Smith ,  Gregory Terrence Garay ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/02

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

公开(公告)号：US20210404344A1

公开(公告)日：2021-12-30

申请号：US17316026

申请日：2021-05-10

Applicant: General Electric Company

Inventor： Thomas Earl Dyson ,  Nicholas William Rathay ,  Brendon James Leary ,  Gregory Terrence Garay ,  Gustavo Adolfo Ledezma ,  David Wayne Weber ,  Aaron Ezekiel Smith

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/14

Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

公开(公告)号：US10927682B2

公开(公告)日：2021-02-23

申请号：US15814996

申请日：2017-11-16

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Fernando Reiter ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F02C7/141 ,  F01D5/14

Abstract: An apparatus and method for a component for a turbine engine, which generates a hot gas flow, and provides a cooling fluid flow, comprising a wall separating the hot gas flow from the cooling fluid flow and having a heated surface along which the hot gas flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising a connecting passage extending between an inlet at the cooled surface and an outlet located at the heated surface, with the connecting passage comprising a diffusing section.

公开(公告)号：US10718217B2

公开(公告)日：2020-07-21

申请号：US15622266

申请日：2017-06-14

Applicant: General Electric Company

Inventor： Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Tingfan Pang ,  Aaron Ezekiel Smith

IPC: F01D5/18 ,  F23R3/00 ,  F01D5/14

Abstract: An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.

公开(公告)号：US10400608B2

公开(公告)日：2019-09-03

申请号：US15360529

申请日：2016-11-23

Applicant: General Electric Company

Inventor： Jessica Elizabeth Coomer ,  Matthew Thomas Beyer ,  Stephen Molter ,  Aaron Ezekiel Smith

IPC: F01D5/18 ,  F01D5/30 ,  F01D5/20

Abstract: A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.

公开(公告)号：US20180291742A1

公开(公告)日：2018-10-11

申请号：US15481628

申请日：2017-04-07

Applicant: General Electric Company

Inventor： James Michael Hoffman ,  Weston Nolan Dooley ,  Aaron Ezekiel Smith ,  Steven Robert Brassfield

IPC: F01D5/08 ,  F01D5/18

Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.

公开(公告)号：US10060269B2

公开(公告)日：2018-08-28

申请号：US14977270

申请日：2015-12-21

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith ,  Gregory Thomas Foster

IPC: F01D5/18 ,  F02C3/04 ,  F02C7/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/204 ,  Y02T50/676

Abstract: A cooling system according to an embodiment includes: a leading edge cooling circuit including a pressure side serpentine circuit and a suction side serpentine circuit; a first mid-blade cooling circuit including a suction side serpentine circuit; a second mid-blade cooling circuit including a pressure side serpentine circuit; a trailing edge cooling circuit; and at least one air feed for supplying cooling air to the leading edge cooling circuit, the first mid-blade cooling circuit, the second mid-blade cooling circuit, and the trailing edge cooling circuit.

公开(公告)号：US20170370229A1

公开(公告)日：2017-12-28

申请号：US15194855

申请日：2016-06-28

Applicant: General Electric Company

Inventor： Gregory Terrence Garay ,  Douglas Ray Smith ,  Aaron Ezekiel Smith ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D9/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F01D25/12

CPC classification number: F01D5/186 ,  B22C9/00 ,  B22C13/085

Abstract: An apparatus and method for forming a film hole in an outer wall of an airfoil. The film hole includes a blind opening adjacent the interior of the airfoil and a hole adjacent the exterior of the airfoil. The blind opening fluidly couples to the hole to form the film hole for providing a volume of fluid as a surface cooling film along the exterior of the outer wall.

公开(公告)号：US09739155B2

公开(公告)日：2017-08-22

申请号：US14143537

申请日：2013-12-30

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith ,  Lisa Anne Wichmann

IPC: F01D5/08 ,  F01D5/18

CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade further may include a rib configuration that partitions the chamber of the airfoil into radially extending flow passages. A first flow passage may include a first side on which turbulators are positioned, wherein each of the turbulators comprises a canted configuration.