公开(公告)号：US10358928B2

公开(公告)日：2019-07-23

申请号：US15150528

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/28

Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

公开(公告)号：US10343218B2

公开(公告)日：2019-07-09

申请号：US15056525

申请日：2016-02-29

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Ronald Scott Bunker ,  Douglas Gerard Konitzer

IPC: B33Y10/00 ,  B33Y80/00 ,  B22C9/04 ,  B22F3/105 ,  B22F3/15 ,  B22F5/00 ,  B22F5/10 ,  B22F7/06 ,  B22F7/08 ,  B28B1/00

Abstract: The present disclosure generally relates to casting molds including a casting shell surrounding at least a portion of a casting core comprising a first metal component and a hot isostactic pressed second metal component around the first metal component. In one aspect, the first metal component may have a lower melting point than the second metal component. In another aspect, the second metal component may retain some metal powder grain structure.

公开(公告)号：US10260354B2

公开(公告)日：2019-04-16

申请号：US15042611

申请日：2016-02-12

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  B33Y10/00 ,  B33Y80/00 ,  B22D25/02 ,  B22F3/105 ,  B22F5/04 ,  B23K20/02 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12 ,  B23K101/00

Abstract: A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.

公开(公告)号：US10233775B2

公开(公告)日：2019-03-19

申请号：US14881188

申请日：2015-10-13

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

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

Abstract: An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. A film hole in the wall has an inlet, an outlet, and a passage connecting the inlet and outlet that defines an inflection point.

公开(公告)号：US10132166B2

公开(公告)日：2018-11-20

申请号：US14633167

申请日：2015-02-27

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Robert David Briggs

IPC: F01D5/18 ,  F01D5/14 ,  F23R3/00 ,  F01D9/06 ,  F01D9/02 ,  F23R3/50

Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.

公开(公告)号：US20180111200A1

公开(公告)日：2018-04-26

申请号：US15298999

申请日：2016-10-20

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: B22F3/11 ,  F01D5/18 ,  F01D5/28 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00 ,  B28B1/00 ,  B22F5/04

CPC classification number: B22F5/04 ,  B22F3/1055 ,  B22F7/004 ,  B22F7/08 ,  B28B1/001 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/183 ,  F01D5/186 ,  F01D5/187 ,  F01D5/28 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/22 ,  F05D2230/31 ,  F05D2260/202 ,  Y02P10/295 ,  Y02T50/676

Abstract: A method of forming a cooling hole structure on a turbine component having a component wall with inner and outer surfaces, wherein a cooling hole passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of forming a recess communicating with the hole and the outer surface; and using an additive manufacturing process to form a porous structure in the recess.

公开(公告)号：US20180051580A1

公开(公告)日：2018-02-22

申请号：US15238233

申请日：2016-08-16

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D11/04 ,  F01D11/00 ,  F01D25/12

CPC classification number: F01D11/04 ,  F01D11/001 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/20 ,  F05D2300/514 ,  F05D2300/612

Abstract: An apparatus relating to a rim seal for turbine engine comprising a wing and discourager extending into a cavity to form a labyrinth fluid path. The wing and discourager can each include a radial extension. Cooling air can pass through the rim seal along the labyrinth fluid path to resist the ingestion of hot gas from a mainstream flow.

公开(公告)号：US20180051568A1

公开(公告)日：2018-02-22

申请号：US15238113

申请日：2016-08-16

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F23R3/06

CPC classification number: F01D5/186 ,  F01D5/183 ,  F01D9/065 ,  F05D2220/32 ,  F05D2230/22 ,  F05D2260/202 ,  F05D2260/203 ,  F05D2300/514 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03041 ,  Y02T50/676

Abstract: An apparatus and method for cooling an engine component, including an outer wall separating a hot fluid flow from a cooling fluid flow, using the cooling fluid flow to cool the engine component. A region in the component can include a plurality of film holes with a porous material to meter the flow of cooling fluid provided from the engine component.

公开(公告)号：US20180051565A1

公开(公告)日：2018-02-22

申请号：US15238150

申请日：2016-08-16

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F01D25/12 ,  F04D29/54 ,  F04D29/58 ,  F04D29/32 ,  F02K3/06

CPC classification number: F01D5/183 ,  F01D5/28 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F02K3/06 ,  F04D29/324 ,  F04D29/542 ,  F04D29/582 ,  F04D29/5846 ,  F05D2220/30 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/232 ,  F05D2250/294 ,  F05D2260/203 ,  F05D2260/232 ,  F05D2300/514 ,  F05D2300/612 ,  Y02T50/676

Abstract: An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

公开(公告)号：US20170362943A1

公开(公告)日：2017-12-21

申请号：US15182651

申请日：2016-06-15

Applicant: General Electric Company

Inventor： Shawn Michael Pearson ,  Kirk Douglas Gallier ,  Ronald Scott Bunker

IPC: F01D5/28 ,  F01D5/18 ,  F02C3/04

CPC classification number: F01D5/282 ,  F01D5/187 ,  F05D2260/941 ,  F05D2300/5024 ,  F05D2300/522 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.