公开(公告)号：US11639664B2

公开(公告)日：2023-05-02

申请号：US17837086

申请日：2022-06-10

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：US11566527B2

公开(公告)日：2023-01-31

申请号：US16223735

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/14 ,  F01D5/18

Abstract: A component, such as for a turbine engine, can include an airfoil with 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. The component can also include at least one cooling passage within the interior.

公开(公告)号：US11499433B2

公开(公告)日：2022-11-15

申请号：US16223279

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster

IPC: F01D5/18 ,  F01D5/30

Abstract: A turbine engine airfoil and method of cooling includes 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. The airfoil can also include at least one cooling conduit and an impingement zone located within the at least one cooling conduit.

公开(公告)号：US11384642B2

公开(公告)日：2022-07-12

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：US11377963B2

公开(公告)日：2022-07-05

申请号：US17183627

申请日：2021-02-24

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：US11359494B2

公开(公告)日：2022-06-14

申请号：US16532787

申请日：2019-08-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Kirk Douglas Gallier ,  Daniel Lee Durstock ,  Zachary Daniel Webster ,  Gregory Terrence Garay

IPC: F01D5/18

Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.

公开(公告)号：US11299998B2

公开(公告)日：2022-04-12

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: F01D9/04 ,  F01D11/00

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：US20210180459A1

公开(公告)日：2021-06-17

申请号：US17183627

申请日：2021-02-24

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：US10981217B2

公开(公告)日：2021-04-20

申请号：US16195089

申请日：2018-11-19

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 ,  B33Y10/00 ,  B33Y80/00 ,  B33Y50/00

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：US10767492B2

公开(公告)日：2020-09-08

申请号：US16223808

申请日：2018-12-18

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18

Abstract: A component, such as for a turbine engine, can include an airfoil with 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. The component can also include at least one cooling passage within the interior.