公开(公告)号：US20180340429A1

公开(公告)日：2018-11-29

申请号：US15604074

申请日：2017-05-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Jacob John KITTLESON ,  John McConnell DELVAUX

IPC: F01D5/28 ,  F01D5/30

Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.

公开(公告)号：US20180229451A1

公开(公告)日：2018-08-16

申请号：US15433548

申请日：2017-02-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Jason Robert PAROLINI ,  John McConnell DELVAUX ,  Canan Uslu HARDWICKE ,  Glenn Curtis TAXACHER ,  James Joseph MURRAY

IPC: B29C70/44 ,  B29D99/00 ,  F01D25/00

CPC classification number: B29C70/44 ,  B29C70/025 ,  B29D99/0028 ,  B32B18/00 ,  C04B35/806 ,  C04B37/001 ,  C04B2235/94 ,  C04B2235/95 ,  C04B2237/38 ,  F01D25/005 ,  F05D2260/202 ,  F05D2300/6033

Abstract: A method of forming a pre-form ceramic matrix composite mold for a ceramic matrix composite (CMC) component including providing pieces of CMC remnant scrap material and randomly arranging the pieces of CMC remnant scrap material relative to one another. The method further includes debulking the pieces of CMC remnant scrap material into a rigidized shape, the rigidized shape having gaps between adjacent pieces of CMC remnant scrap material of about 10 microns and about 10 mm and a gap spacing between about 50 microns and about 50 mm, and forming the rigidized shape into a mold.

公开(公告)号：US20150345388A1

公开(公告)日：2015-12-03

申请号：US14292969

申请日：2014-06-02

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Paul Stephen DIMASCIO ,  Victor John MORGAN ,  Jason Robert PAROLINI ,  Glenn Curtis TAXACHER ,  Frederic Woodrow ROBERTS, JR. ,  Jacob John KITTLESON ,  John McConnell DELVAUX

IPC: F02C7/00 ,  B23K1/00 ,  B23P6/00 ,  C04B41/91 ,  B24B33/00 ,  C04B41/00 ,  C04B41/53 ,  C04B41/50 ,  C04B41/45 ,  C23C16/24 ,  C04B41/85

CPC classification number: F02C7/00 ,  B23K1/0018 ,  B23P6/002 ,  B23P6/007 ,  B24B33/00 ,  C04B41/009 ,  C04B41/4531 ,  C04B41/5025 ,  C04B41/5096 ,  C04B41/5144 ,  C04B41/53 ,  C04B41/85 ,  C04B41/87 ,  C04B41/88 ,  C04B41/91 ,  C23C16/24 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2300/6033 ,  Y10T156/10 ,  Y10T428/24355 ,  C04B35/00 ,  C04B35/80 ,  C04B41/4529 ,  C04B41/4539 ,  C04B41/5133 ,  C04B41/0072

Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.

Abstract translation: 提供了陶瓷基复合燃气轮机部件和陶瓷基复合燃气轮机部件的制造方法。 该方法包括改变陶瓷基复合燃气轮机部件的表面以产生表面粗糙度小于6微米的改性表面。 修饰选自由将未增强的基质层施加到表面，在表面上蒸镀硅，珩磨表面，将钎焊膏施加到表面上的技术组合，以及它们的组合。 该组件包括包括小于6微米的表面粗糙度的改性表面。 所述改性表面选自施加到陶瓷基复合燃气轮机部件的表面的未增强基体层，沉积在表面上的硅蒸汽表面，珩磨表面，施加到表面上的钎焊膏及其组合。

公开(公告)号：US20180363483A1

公开(公告)日：2018-12-20

申请号：US15623696

申请日：2017-06-15

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy HAFNER ,  John McConnell DELVAUX ,  Glenn Curtis TAXACHER

IPC: F01D9/04

Abstract: A turbine component includes an outer shroud arranged within a turbine and further including opposed extending portions. The component further provides an inner shroud shielding the outer shroud from a gas path within the turbine during operation of the turbine and including opposed arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud for supporting the inner shroud from the outer shroud. The component further provides a load path forming region at least partially extending between facing surfaces of each arcuate portion and corresponding extending portion. During operation of the turbine, load path forming regions extend into direct contact between at least a portion of the facing surfaces of each arcuate portion and corresponding extending portion, resulting in formation of a loading arrangement having generally evenly distributed radial load forces at the load path forming regions.

公开(公告)号：US20180099467A1

公开(公告)日：2018-04-12

申请号：US14734028

申请日：2015-06-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Philip Harold MONAGHAN ,  John McConnell DELVAUX ,  Glenn Curtis TAXACHER

IPC: B29D99/00 ,  F01D5/28

CPC classification number: B29D99/0028 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/222 ,  Y10T29/4998

Abstract: A pre-form CMC cavity and method of forming pre-form CMC cavity for a ceramic matrix component includes providing a mandrel, applying a base ply to the mandrel, laying-up at least one CMC ply on the base ply, removing the mandrel, and densifying the base ply and the at least one CMC ply. The remaining densified base ply and at least one CMC ply form a ceramic matrix component having a desired geometry and a cavity formed therein. Also provided is a method of forming a CMC component.

公开(公告)号：US20170350260A1

公开(公告)日：2017-12-07

申请号：US15174271

申请日：2016-06-06

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip DUTTA ,  James ZHANG ,  Gary Michael ITZEL ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

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

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D5/282 ,  F01D9/02 ,  F01D25/12 ,  F05D2220/30 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/185 ,  F05D2260/20 ,  F05D2260/204 ,  F05D2300/175 ,  F05D2300/6033

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

公开(公告)号：US20170328203A1

公开(公告)日：2017-11-16

申请号：US15150573

申请日：2016-05-10

Applicant: GENERAL ELECTRIC COMPANY

Inventor： James ZHANG ,  James Tyson BALKCUM, III ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

IPC: F01D1/04

CPC classification number: F01D1/04 ,  F01D11/001 ,  F01D11/008 ,  F05D2240/11 ,  F05D2240/55

Abstract: A turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a tip distal from the outer wall segment such that the tips form a seal with the inner wall segments at an inner flow path of the turbine. An inner wall assembly and a turbine assembly method are also disclosed.

公开(公告)号：US20170276021A1

公开(公告)日：2017-09-28

申请号：US15080201

申请日：2016-03-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy HAFNER ,  Gary Michael ITZEL ,  John McConnell DELVAUX ,  Sandip DUTTA

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

Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.

公开(公告)号：US20150147184A1

公开(公告)日：2015-05-28

申请号：US14088612

申请日：2013-11-25

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Peter de DIEGO ,  John McConnell DELVAUX ,  Glenn Curtis TAXACHER

IPC: F01D5/28 ,  B28B11/24

CPC classification number: F01D5/282 ,  C04B35/573 ,  C04B35/65 ,  C04B35/806 ,  F01D5/081 ,  F01D5/18 ,  F01D5/284 ,  F01D5/3007 ,  F05D2300/6033

Abstract: A process of producing a ceramic matrix composite turbine bucket, an insert for a ceramic matrix composite turbine bucket, and a ceramic matrix composite turbine bucket are disclosed. The process includes providing a bucket preform having a dovetail cavity, the dovetail cavity being enclosed within a dovetail shank of the bucket preform, positioning an insert within the dovetail cavity, then forming the ceramic matrix composite turbine bucket in a furnace. The insert includes a geometry configured to be fit within a dovetail cavity of the ceramic matrix composite turbine bucket, a bucket preform, or both. The insert is foam material or a plurality of ceramic matrix composite plies. The ceramic matrix composite turbine bucket includes a dovetail shank and a dovetail cavity enclosed within the dovetail shank. The dovetail cavity is arranged and disposed for receiving an insert.

Abstract translation: 公开了一种制备陶瓷基复合涡轮机桶，陶瓷基复合涡轮机叶片嵌件和陶瓷基复合涡轮机桶的方法。 该方法包括提供具有燕尾腔的料斗预制件，燕尾槽被封闭在料斗预制件的燕尾柄内，将插入件定位在燕尾槽内，然后在炉中形成陶瓷基复合涡轮机桶。 插入件包括被配置为配合在陶瓷基复合涡轮机桶，桶预制件或二者的燕尾槽内的几何形状。 插入件是泡沫材料或多个陶瓷基复合层。 陶瓷基复合涡轮机桶包括燕尾柄和燕尾榫柄内的燕尾腔。 燕尾腔布置和布置成用于接收插入物。

公开(公告)号：US20200182067A1

公开(公告)日：2020-06-11

申请号：US16787819

申请日：2020-02-11

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Sandip DUTTA ,  James ZHANG ,  Gary Michael ITZEL ,  John McConnell DELVAUX ,  Matthew Troy HAFNER

IPC: F01D5/18 ,  F01D25/12 ,  F01D25/00 ,  F01D9/04 ,  F01D5/28 ,  F01D5/14

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.