公开(公告)号：US20230393554A1

公开(公告)日：2023-12-07

申请号：US18453746

申请日：2023-08-22

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Tingfan Pang ,  Gregory Terrence Garay ,  Xi Yang ,  Daniel Lee Durstock ,  Steven Robert Brassfield ,  William Charles Herman

IPC: G05B19/4099 ,  B29C64/393 ,  G06F30/10

CPC classification number: G05B19/4099 ,  B29C64/393 ,  G06F30/10 ,  G05B2219/35036 ,  G05B2219/35134 ,  G05B2219/49007

Abstract: A method of forming a component that includes identifying an acute angle in an original model that is a virtual model of the component. The acute angle is defined by a first surface and a second surface. The method includes compensating the original model at the acute angle to create a compensated acute angle in a compensated model. The method also includes forming, by additive manufacturing, the component based upon the compensated model, where the formed component is more alike the original model than the compensated model.

公开(公告)号：US11448076B2

公开(公告)日：2022-09-20

申请号：US17213771

申请日：2021-03-26

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：US20220228493A1

公开(公告)日：2022-07-21

申请号：US17714629

申请日：2022-04-06

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/30

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

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：US11131213B2

公开(公告)日：2021-09-28

申请号：US16733377

申请日：2020-01-03

Applicant: General Electric Company

Inventor： Kelli Marie Fishback ,  Jonathan Russell Ratzlaff ,  Steven Robert Brassfield ,  Kurt Thomas Whittington

IPC: F01D5/12 ,  F01D25/12

Abstract: An airfoil assembly for a turbine engine that includes a platform, a dovetail, an airfoil. The airfoil assembly can further include a cooling air circuit that fluidly connects to a platform cooling passage. The cooling air circuit and platform cooling passage can be contained within or housed at least in part by the platform, the dovetail, or the airfoil. The cooling air circuit can also include a deflector.

公开(公告)号：US11021969B2

公开(公告)日：2021-06-01

申请号：US16214411

申请日：2018-12-10

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield

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

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

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：US20210079808A1

公开(公告)日：2021-03-18

申请号：US16568821

申请日：2019-09-12

Applicant: General Electric Company

Inventor： Daniel Endicott Osgood ,  Gregory Terrence Garay ,  Daniel Lee Durstock ,  Steven Robert Brassfield ,  Tingfan Pang

IPC: F01D25/12 ,  F23R3/00

Abstract: The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.

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：US10697301B2

公开(公告)日：2020-06-30

申请号：US15481659

申请日：2017-04-07

Applicant: General Electric Company

Inventor： James Michael Hoffman ,  Weston Nolan Dooley ,  Matthew Lee Krumanaker ,  Aaron Ezekiel Smith ,  Steven Robert Brassfield

IPC: F01D5/08 ,  F01D5/18

Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.