公开(公告)号：US11035237B2

公开(公告)日：2021-06-15

申请号：US16793138

申请日：2020-02-18

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 ,  F01D5/30

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：US11015453B2

公开(公告)日：2021-05-25

申请号：US15820568

申请日：2017-11-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D5/20 ,  F01D9/04 ,  F01D25/12 ,  F04D29/32 ,  F04D29/58 ,  F04D29/54 ,  F02C3/04 ,  F02C7/18

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.

公开(公告)号：US10830057B2

公开(公告)日：2020-11-10

申请号：US15609488

申请日：2017-05-31

Applicant: General Electric Company

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

IPC: F01D5/20 ,  F01D5/18

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

公开(公告)号：US20200300097A1

公开(公告)日：2020-09-24

申请号：US16793138

申请日：2020-02-18

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：US10753207B2

公开(公告)日：2020-08-25

申请号：US15648564

申请日：2017-07-13

Applicant: General Electric Company

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

IPC: F01D5/18 ,  F01D5/20

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil 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 airfoil to cool the tip of the airfoil.

公开(公告)号：US10648342B2

公开(公告)日：2020-05-12

申请号：US15844684

申请日：2017-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Aaron Ezekiel Smith ,  Steven Robert Brassfield

IPC: F01D5/18 ,  F01D5/14 ,  F23R3/00

Abstract: An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes at least one cooling hole including a diffusing section and fluidly coupling an exterior of the engine component to an exterior of the engine component.

公开(公告)号：US20190153873A1

公开(公告)日：2019-05-23

申请号：US15820568

申请日：2017-11-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Aaron Ezekiel Smith ,  Matthew Thomas Beyer ,  Gregory Terrence Garay ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F02C3/04 ,  F02C7/18

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.

公开(公告)号：US20190085705A1

公开(公告)日：2019-03-21

申请号：US15707303

申请日：2017-09-18

Applicant: General Electric Company

Inventor： Zachary Daniel Webster ,  Daniel Scott Martyn ,  Aaron Ezekiel Smith ,  Kirk D. Gallier

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

Abstract: An apparatus and method relating to a film-hole of a component of a turbine engine. The film-hole can extend from an inlet to an outlet to define a passage. The film-hole can include a laid back section where a coating can be applied. The method can include forming the film-hole in the component and applying the coating to the component to maintain a specific geometry.

公开(公告)号：US20190017389A1

公开(公告)日：2019-01-17

申请号：US15648564

申请日：2017-07-13

Applicant: General Electric Company

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

IPC: F01D5/18

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall (94) enclosing an interior for the airfoil 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 airfoil to cool the tip of the airfoil.

公开(公告)号：US09926788B2

公开(公告)日：2018-03-27

申请号：US14977247

申请日：2015-12-21

Applicant: General Electric Company

Inventor： Aaron Ezekiel Smith ,  Gregory Thomas Foster ,  David Wayne Weber ,  Joseph Anthony Weber

IPC: F02C7/12 ,  F01D5/18 ,  F02C3/04

CPC classification number: F01D5/187 ,  F01D5/186 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/305 ,  F05D2240/307 ,  F05D2250/185 ,  F05D2260/205

Abstract: A cooling system according to an embodiment includes: a serpentine cooling circuit, the serpentine cooling circuit including a first leg extending in a first direction, a second leg extending in a second direction, and a turn fluidly coupling the first leg and the second leg; and an air feed cavity for supplying cooling air to the serpentine cooling circuit; wherein the first leg of the serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the serpentine cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels of the multi-wall blade.