公开(公告)号：US20190218917A1

公开(公告)日：2019-07-18

申请号：US15873301

申请日：2018-01-17

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F01D25/24

CPC classification number: F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F01D25/24 ,  F05D2260/202 ,  F05D2260/2212

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, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.

公开(公告)号：US20180291742A1

公开(公告)日：2018-10-11

申请号：US15481628

申请日：2017-04-07

Applicant: General Electric Company

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

IPC: F01D5/08 ,  F01D5/18

Abstract: An airfoil assembly for a turbine engine can comprise a platform having first and second opposing surfaces, an airfoil extending from the first surface, a base extending from the second surface, and a platform cooling circuit including a feed tube, a first branch, a second branch, and a flow divider.

公开(公告)号：US20180209277A1

公开(公告)日：2018-07-26

申请号：US15412387

申请日：2017-01-23

Applicant: General Electric Company

Inventor： Weston Nolan Dooley ,  James Michael Hoffman ,  Steven Robert Brassfield

IPC: F01D5/18 ,  B22C9/10 ,  B22C9/24 ,  B22C9/04 ,  B22C7/02 ,  B22D25/06 ,  B22D29/00

Abstract: An apparatus relating to engineering the geometry for a ball-chute support feature in an investment casting core. The investment casting core is for an airfoil region having at least one serpentine feature and at least one inlet feature coupled to the at least one serpentine feature by a ball-chute support feature. The investment casting core is leached out to form cooling passages in the airfoil.

公开(公告)号：US20170107828A1

公开(公告)日：2017-04-20

申请号：US14884100

申请日：2015-10-15

Applicant: General Electric Company

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

IPC: F01D5/18 ,  F01D5/14

Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.

公开(公告)号：US20170107824A1

公开(公告)日：2017-04-20

申请号：US14884009

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Steven Robert Brassfield ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18 ,  F01D25/12 ,  F04D29/54 ,  F04D29/58 ,  F01D9/04 ,  F04D29/32

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/18 ,  F01D9/041 ,  F01D25/12 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/185 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/676

Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

公开(公告)号：US11782416B2

公开(公告)日：2023-10-10

申请号：US16871186

申请日：2020-05-11

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 using additive manufacturing to form or print a component based on an original model of a component, where the geometry of the original model is compensated to form a compensated model. The compensated model can be used to form or print the component. The printed component as a final model can then be compared to the original model.

公开(公告)号：US20220403745A1

公开(公告)日：2022-12-22

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：US11480058B2

公开(公告)日：2022-10-25

申请号：US17029807

申请日：2020-09-23

Applicant: GENERAL ELECTRIC COMPANY

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

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/24 ,  F01D25/12 ,  F01D9/06

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, a set of cooling holes having an inlet fluidly coupled to the cooling passage, an outlet located on one of the pressure side or suction side, with a connecting passage fluidly coupling the inlet to the outlet.

公开(公告)号：US20210239005A1

公开(公告)日：2021-08-05

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：US20210207493A1

公开(公告)日：2021-07-08

申请号：US16733377

申请日：2020-01-03

Applicant: General Electric Company

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

IPC: F01D25/12 ,  F01D5/12

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.