公开(公告)号：US20210148242A1

公开(公告)日：2021-05-20

申请号：US17158670

申请日：2021-01-26

Applicant: General Electric Company

Inventor： Ryan Christopher Jones ,  Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Tingfan Pang

IPC: F01D11/00 ,  F01D9/04

Abstract: A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

公开(公告)号：US10941671B2

公开(公告)日：2021-03-09

申请号：US15467431

申请日：2017-03-23

Applicant: General Electric Company

Inventor： Weston Nolan Dooley ,  James Michael Hoffman ,  Gregory Terrence Garay

IPC: F01D11/00 ,  F01D5/30

Abstract: A turbine engine component includes: a body bounded by an end face; and a seal slot having an opening communicating with the end face, the seal slot including a receptacle defining a boundary configured to receive and position a spline seal, and an open chamber communicating with the seal slot and extending beyond the boundary.

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：US20200347735A1

公开(公告)日：2020-11-05

申请号：US16929936

申请日：2020-07-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Steven Robert Brassfield ,  Gregory Terrence Garay ,  Tingfan Pang ,  Daniel Endecott Osgood

IPC: F01D5/18

Abstract: An airfoil for a turbine engine, comprising an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction, outlets on the exterior surface, and a cooling air supply conduit within the interior and having a supply passage.

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：US10717130B2

公开(公告)日：2020-07-21

申请号：US15439548

申请日：2017-02-22

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Mark Kevin Meyer ,  Douglas Gerard Konitzer ,  William Thomas Carter

IPC: B22F5/04 ,  B22F3/105 ,  B22F7/08 ,  B22F7/06 ,  B22D29/00 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/00 ,  F01D5/18 ,  B22D25/02 ,  B22F5/10

Abstract: Methods of manufacturing or repairing a turbine blade or vane are described. The airfoil portions of these turbine components are typically manufactured by casting in a ceramic mold, and a surface made up of the cast airfoil and at the least the ceramic core serves as a build surface for a subsequent process of additively manufacturing the tip portions. The build surface is created by removing a top portion of the airfoil and the core, or by placing an ultra-thin shim on top of the airfoil and the core. The overhang projected by the shim is subsequently removed. These methods are not limited to turbine engine applications, but can be applied to any metallic object that can benefit from casting and additive manufacturing processes. The present disclosure also relates to finished and intermediate products prepared by these methods.

公开(公告)号：US20200072059A1

公开(公告)日：2020-03-05

申请号：US16120758

申请日：2018-09-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Gregory Terrence Garay ,  Xi Yang ,  Tingfan Pang ,  Steven Robert Brassfield

IPC: F01D5/18

Abstract: An apparatus and method for cooling a component for a turbine engine which generates a hot gas flow and provides a cooling fluid flow, the component comprising a body having an outer surface, at least a portion of which is exposed to the hot gas flow to define a hot surface, a cooling cavity located within the body and fluidly coupled to the cooling fluid flow and a pin located within the cooling cavity and defining a cooling hole.

公开(公告)号：US20190257206A1

公开(公告)日：2019-08-22

申请号：US15898703

申请日：2018-02-19

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Zachary Daniel Webster ,  Gregory Terrence Garay ,  Steven Robert Brassfield

IPC: F01D5/18

Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

公开(公告)号：US20190249554A1

公开(公告)日：2019-08-15

申请号：US15895157

申请日：2018-02-13

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Tingfan Pang ,  Helen Ogbazion Gabregiorgish ,  Zachary Daniel Webster ,  Steven Robert Brassfield

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

CPC classification number: F01D5/187 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/323 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/202

Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage, an outlet located proximate the leading edge, with a connecting passage fluidly coupling the inlet to the outlet.