公开(公告)号：US20240175364A1

公开(公告)日：2024-05-30

申请号：US18432818

申请日：2024-02-05

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/14 ,  F01D25/12 ,  F01D25/14 ,  F23C7/02

CPC classification number: F01D5/147 ,  F01D25/12 ,  F01D25/14 ,  F23C7/02 ,  F05D2300/60 ,  F05D2300/70

Abstract: A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.

公开(公告)号：US11235491B2

公开(公告)日：2022-02-01

申请号：US16531731

申请日：2019-08-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Xi Yang ,  Michael Cole ,  Michael Brown ,  Gregory Terrence Garay ,  Tingfan Pang ,  Brian David Przeslawski ,  Douglas Gerard Konitzer

IPC: B22C9/04 ,  B22C9/10 ,  B28B1/00 ,  B33Y10/00 ,  B28B7/28 ,  F01D5/14 ,  B22C7/02 ,  B22C9/08 ,  B28B7/34 ,  F01D5/18

Abstract: Integrated core-shell investment casting molds include a filament structure corresponding to a cooling hole pattern in the surface of the turbine blade, stator vane, or shroud.

公开(公告)号：US11174736B2

公开(公告)日：2021-11-16

申请号：US16224065

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Tingfan Pang ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/30 ,  B22F10/20 ,  B33Y10/00 ,  B33Y80/00 ,  B22F10/30

Abstract: Aspects generally relate to a method of forming a plexus within an additively-manufactured component. The method includes forming a fluid passage in the plexus by serially forming layers of material along a build direction to form a column defining the fluid passage along a first direction within an interior of a turbine engine component.

公开(公告)号：US11130170B2

公开(公告)日：2021-09-28

申请号：US15887601

申请日：2018-02-02

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Gregory Terrence Garay ,  Meredith Dubelman ,  Xi Yang ,  Tingfan Pang ,  Michael Scott Cole ,  Brian David Przeslawski ,  Douglas Gerard Konitzer ,  Nicole Barba ,  Kirk Gallier ,  Brian Keith

IPC: B22C9/22 ,  B22D29/00 ,  B28B1/00 ,  B33Y10/00 ,  F01D5/18 ,  F01D9/02 ,  B33Y80/00 ,  C30B29/02

Abstract: Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.

公开(公告)号：US20210220904A1

公开(公告)日：2021-07-22

申请号：US17221911

申请日：2021-04-05

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: B22C9/10 ,  B22C9/12 ,  B22C9/26 ,  B22C7/02 ,  B22C21/14 ,  F01D5/18 ,  B28B7/34 ,  B28B1/00

Abstract: A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.

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：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：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：US20200040753A1

公开(公告)日：2020-02-06

申请号：US16055987

申请日：2018-08-06

Applicant: General Electric Company

Inventor： Ryan Christopher Jones ,  Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory T. 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：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.