公开(公告)号：US11236618B2

公开(公告)日：2022-02-01

申请号：US17082288

申请日：2020-10-28

Applicant: General Electric Company

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

IPC: F01D5/18

Abstract: An airfoil for a turbine engine can include an outer wall 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. A plurality of outlets and a plurality of scalloped portions can extend along the outer wall.

公开(公告)号：US11021968B2

公开(公告)日：2021-06-01

申请号：US16195048

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: B22C9/04 ,  F01D5/18 ,  B22C9/26 ,  B22C21/14 ,  B22D25/02 ,  B33Y80/00

Abstract: A cast component having reduced cross flow linking cavities and method of casting may include a body. The body may define a plurality of internal flow channels. The plurality of internal flow channels may include a first internal flow channel and a second internal flow channel. The cast component may also include a plurality of linking cavities obstructing unintended fluid communication between the first internal flow channel and the second internal flow channel through the plurality of linking cavities.

公开(公告)号：US10975704B2

公开(公告)日：2021-04-13

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：US10927692B2

公开(公告)日：2021-02-23

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: 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：US20210040859A1

公开(公告)日：2021-02-11

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：US20200332659A1

公开(公告)日：2020-10-22

申请号：US16386972

申请日：2019-04-17

Applicant: General Electric Company

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

IPC: F01D5/18

Abstract: An airfoil for a turbine engine can include an outer wall 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. A plurality of outlets and a plurality of scalloped portions can extend proximate the trailing edge.

公开(公告)号：US10760431B2

公开(公告)日：2020-09-01

申请号：US15697886

申请日：2017-09-07

Applicant: General Electric Company

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

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D9/06 ,  F01D9/02 ,  F02K1/82 ,  F23R3/00

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：US20200157947A1

公开(公告)日：2020-05-21

申请号：US16195048

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: F01D5/18 ,  B22C9/04 ,  B22C9/26 ,  B22C21/14 ,  B22D25/02

Abstract: A cast component having reduced cross flow linking cavities and method of casting may include a body. The body may define a plurality of internal flow channels. The plurality of internal flow channels may include a first internal flow channel and a second internal flow channel. The cast component may also include a plurality of linking cavities obstructing unintended fluid communication between the first internal flow channel and the second internal flow channel through the plurality of linking cavities.

公开(公告)号：US20200040743A1

公开(公告)日：2020-02-06

申请号：US16055292

申请日：2018-08-06

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann

IPC: F01D5/18 ,  F01D5/14

Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

公开(公告)号：US20190316473A1

公开(公告)日：2019-10-17

申请号：US16423313

申请日：2019-05-28

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Zachary Daniel Webster

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

Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.