公开(公告)号：US20140083639A1

公开(公告)日：2014-03-27

申请号：US13705758

申请日：2012-12-05

Applicant: General Electric Company

Inventor： Eric Richard Bonini ,  Ronald Scott Bunker

IPC: B22D25/02

CPC classification number: B23P15/02 ,  B22D15/02 ,  B22D25/02 ,  B23H9/14 ,  B23H9/16 ,  B23K15/085 ,  B23K26/382 ,  B23K26/40 ,  B23K2103/02 ,  B23K2103/08 ,  B23K2103/16 ,  B23K2103/26 ,  B23P2700/06 ,  F01D5/187 ,  F05D2230/13 ,  F05D2230/21 ,  F05D2260/202 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49815

Abstract: A method of machining a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. A core is disposed within each interior space. The method includes forming at least one hole in the substrate while the core is disposed within the respective interior space. Each hole extends through the substrate to provide fluid communication with the respective interior space. The method further includes removing the core from the respective interior space. The core may be a casting core or a subsequently formed core.

Abstract translation: 提供了一种加工部件的方法。 该部件包括具有外表面和内表面的基底，其中内表面限定至少一个内部空间。 每个内部空间内设置核心。 所述方法包括在所述芯设置在相应的内部空间内时在所述基板中形成至少一个孔。 每个孔延伸穿过衬底以提供与相应内部空间的流体连通。 该方法还包括从相应的内部空间移除芯。 芯可以是铸芯或随后形成的芯。

公开(公告)号：US20140004310A1

公开(公告)日：2014-01-02

申请号：US14017605

申请日：2013-09-04

Applicant: General Electric Company

Inventor： Raul Basilio Rebak ,  Renee Bushey Rohling ,  Scott Andrew Weaver ,  Ronald Scott Bunker ,  Don Mark Lipkin ,  Lawrence Bernard Kool

IPC: F01D25/08 ,  B81B1/00

CPC classification number: F01D25/08 ,  B81B1/002 ,  C23C4/02 ,  C23C4/073 ,  C23C4/18 ,  C23C14/028 ,  C23C14/16 ,  C23C14/5873 ,  F01D5/184 ,  F01D5/187 ,  F05D2230/10 ,  F05D2230/90 ,  F05D2260/202 ,  F05D2260/203 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T83/0304 ,  Y10T428/13 ,  Y10T428/24562 ,  Y10T428/24612 ,  Y10T428/2462

Abstract: Methods of fabricating coated components using multiple types of fillers are provided. One method comprises forming one or more grooves in an outer surface of a substrate. Each groove has a base and extends at least partially along the outer surface of the substrate. The method further includes disposing a sacrificial filler within the groove(s), disposing a permanent filler over the sacrificial filler, disposing a coating over at least a portion of the substrate and over the permanent filler, and removing the first sacrificial filler from the groove(s), to define one or more channels for cooling the component. A component with a permanent filler is also provided.

Abstract translation: 提供使用多种类型的填料制造涂层组分的方法。 一种方法包括在衬底的外表面中形成一个或多个凹槽。 每个凹槽具有基部并且至少部分地沿衬底的外表面延伸。 该方法还包括在凹槽内设置牺牲填料，在永久性填料上方设置永久性填料，在衬底的至少一部分上并在永久性填料上方设置涂层，并将第一牺牲填料从槽 以定义用于冷却部件的一个或多个通道。 还提供了具有永久填料的组分。

公开(公告)号：US20130316100A1

公开(公告)日：2013-11-28

申请号：US13954260

申请日：2013-07-30

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/14 ,  F01D5/18

CPC classification number: F01D5/147 ,  F01D5/186 ,  F05B2230/10 ,  F05B2230/30 ,  F05B2230/90 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49982 ,  Y10T428/13 ,  Y10T428/2457 ,  Y10T428/24612

Abstract: A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.

Abstract translation: 提供了一种制造组件的方法。 该方法包括在衬底的外表面中形成一个或多个凹槽。 每个凹槽至少部分地沿着基底的表面延伸并且具有基部，顶部和至少一个放电点。 该方法还包括形成与每个凹槽相邻的排出点的偏移区域，并在衬底的表面的至少一部分上设置涂层。 凹槽和涂层限定了一个或多个通道用于冷却部件。 还提供带冷却通道的部件。

公开(公告)号：US20130140007A1

公开(公告)日：2013-06-06

申请号：US13753828

申请日：2013-01-30

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Bin Wei ,  Mitchell Nile Hammond

IPC: F28F13/18

CPC classification number: F28F13/18 ,  B23P15/04 ,  B23P2700/13 ,  B24C1/04 ,  C23C4/02 ,  C23C4/04 ,  C23C4/12 ,  C23C4/134 ,  C23C14/16 ,  C23C14/32 ,  F01D5/187 ,  F05D2230/10 ,  Y02T50/67 ,  Y02T50/672 ,  Y02T50/676 ,  Y02T50/6765 ,  Y10T29/49339 ,  Y10T29/49341

Abstract: A method of fabricating a component is provided. The method includes forming one or more grooves in a surface of a substrate, where the substrate has at least one hollow interior space. Each of the one or more grooves extends at least partially along the substrate surface and has a base and a top. The base is wider than the top, such that each of the one or more grooves comprises a re-entrant shaped groove. The method further includes forming one or more access holes through the base of a respective groove, to connect the groove in fluid communication with respective ones of the hollow interior space(s), and disposing a coating over at least a portion of the substrate surface. The one or more grooves and coating define one or more re-entrant shaped channels for cooling the component. A component with one or more re-entrant shaped channels and a method of coating a component are also provided.

Abstract translation: 提供了一种制造组件的方法。 该方法包括在衬底的表面中形成一个或多个凹槽，其中衬底具有至少一个中空的内部空间。 所述一个或多个凹槽中的每一个至少部分地沿衬底表面延伸并且具有基部和顶部。 基部比顶部宽，使得一个或多个凹槽中的每一个包括凹入形状的凹槽。 该方法还包括通过相应凹槽的底部形成一个或多个入口孔，以将凹槽与相应的一个中空内部空间流体连通，并且在衬底表面的至少一部分上设置涂层 。 一个或多个凹槽和涂层限定一个或多个凹入形状的通道以冷却部件。 还提供了具有一个或多个重新设计的通道的部件和涂覆部件的方法。

公开(公告)号：US11713682B2

公开(公告)日：2023-08-01

申请号：US16662730

申请日：2019-10-24

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: B33Y10/00 ,  F01D5/18 ,  B22F3/24 ,  B22F10/28 ,  B22F5/04 ,  B22F7/08 ,  F01D25/28 ,  B23K15/00 ,  B23K26/382 ,  B23K26/34 ,  B23K26/384 ,  B22F7/04 ,  C23C24/08 ,  B23K101/00 ,  B23K103/18 ,  B22F10/25 ,  B22F10/68 ,  B22F10/66

CPC classification number: F01D5/186 ,  B22F3/24 ,  B22F5/04 ,  B22F7/04 ,  B22F7/08 ,  B23K15/0086 ,  B23K15/0093 ,  B23K26/34 ,  B23K26/384 ,  B23K26/389 ,  B33Y10/00 ,  C23C24/087 ,  F01D25/285 ,  B22F10/25 ,  B22F10/28 ,  B22F10/66 ,  B22F10/68 ,  B22F2998/10 ,  B22F2999/00 ,  B23K2101/001 ,  B23K2103/26 ,  B23P2700/06 ,  F05D2230/10 ,  F05D2230/31 ,  Y02P10/25 ,  Y02T50/60 ,  B22F2999/00 ,  B22F5/10 ,  B22F2003/247 ,  B22F2998/10 ,  B22F7/08 ,  B22F10/28 ,  B22F10/66 ,  B22F2003/247 ,  B22F10/68 ,  B22F2998/10 ,  B22F7/08 ,  B22F10/25 ,  B22F10/66 ,  B22F2003/247 ,  B22F10/68

Abstract: A method of forming a passage in a turbine component includes: using an additive manufacturing process to form a first support structure on a first surface of the turbine component; forming a second support structure on a second surface of the turbine component, the second support structure being spaced apart from the first support structure; and forming a passage in the turbine component between the first and second support structures.

公开(公告)号：US10946473B2

公开(公告)日：2021-03-16

申请号：US14711816

申请日：2015-05-14

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  William Thomas Carter ,  Wayne Charles Hasz

IPC: B23K15/00 ,  B23K26/342 ,  B22F3/105 ,  B22F5/04

Abstract: A method of forming structure on a component includes: providing a component having a first surface; adhering powder to the first surface; and directing a beam from a directed energy source to fuse the powder in a pattern corresponding to a layer of the structure.

公开(公告)号：US10830051B2

公开(公告)日：2020-11-10

申请号：US14966030

申请日：2015-12-11

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D25/12

Abstract: An engine component can comprise a cooled surface adjacent to a cooling flow and a hot surface adjacent to a hot flow of fluid. The component can comprise a wall separating the hot and cooling flows, defining the cooled surface and the hot surface, and having a plurality of film holes disposed in the wall. At least one turbulator and at least one film hole inlet can be disposed on the cooled surface. The turbulator and the inlet can be arranged to provide a steady flow of cooling fluid to the film hole. One arrangement can comprise spacing the film hole inlet at least two turbulator heights from the turbulator.

公开(公告)号：US10815782B2

公开(公告)日：2020-10-27

申请号：US15191934

申请日：2016-06-24

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: B22F3/105 ,  F01D5/00 ,  F01D5/18 ,  B33Y10/00 ,  B33Y80/00 ,  B23P6/00 ,  B23P6/04 ,  F01D9/02 ,  F01D25/12

Abstract: Methods for repairing a trailing edge of an airfoil are provided. The method can include removing a portion of the trailing edge of the airfoil to form an intermediate component, and then applying using additive manufacturing a replacement portion on the intermediate component to form a repaired airfoil. The replacement portion defines at least one trailing edge ejection slot.

公开(公告)号：US10690055B2

公开(公告)日：2020-06-23

申请号：US15314490

申请日：2015-05-27

Applicant: General Electric Company

Inventor： Curtis Walton Stover ,  Jonathan Michael Rausch ,  Satoshi Atsuchi ,  Gulcharan Singh Brainch ,  Robert David Briggs ,  Ronald Scott Bunker ,  Ambarish Jayant Kulkarni ,  Michael Alan Meade ,  Byron Andrew Pritchard ,  Robert Proctor

IPC: F02C7/18 ,  F01D11/08 ,  F01D25/12 ,  F01D9/04 ,  F01D5/18 ,  F23R3/00

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

公开(公告)号：US10590786B2

公开(公告)日：2020-03-17

申请号：US15144857

申请日：2016-05-03

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Robert Charles Groves, II

IPC: F01D9/06 ,  F01D5/18 ,  F01D25/14 ,  F01D9/04 ,  F01D25/12 ,  F01D25/24

Abstract: A method for cooling a component of a gas turbine engine includes flowing a cooling airflow through a cooling passage of a turbine rotor blade, wherein the cooling passage includes an inlet and an outlet formed on a blade tip of the turbine rotor blade. The method further includes receiving at least a portion of the cooling airflow exiting the outlet of the cooling passage with an aperture defined in a casing of the gas turbine engine, wherein the casing is spaced from the blade tip along the radial direction. In addition, the method includes providing the cooling airflow received with the aperture defined in the casing to the component of the gas turbine engine through a coolant duct assembly of the gas turbine engine.