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：US20170320232A1

公开(公告)日：2017-11-09

申请号：US15146288

申请日：2016-05-04

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Peter de DIEGO

IPC: B28B1/00 ,  C04B35/64 ,  F01D25/00 ,  F01D5/28 ,  C04B35/76 ,  B33Y80/00 ,  B33Y10/00

CPC classification number: B32B1/08 ,  B32B3/263 ,  B32B3/266 ,  B32B5/26 ,  B32B7/04 ,  B32B18/00 ,  B32B2260/023 ,  B32B2260/04 ,  B32B2262/10 ,  B32B2262/105 ,  B32B2262/106 ,  B32B2305/07 ,  B32B2305/076 ,  B32B2305/08 ,  B32B2313/00 ,  B32B2313/02 ,  B32B2313/04 ,  B32B2603/00 ,  C04B35/10 ,  C04B35/52 ,  C04B35/521 ,  C04B35/565 ,  C04B35/64 ,  C04B35/76 ,  C04B37/005 ,  C04B2237/38 ,  C04B2237/385 ,  C04B2237/61 ,  C04B2237/84 ,  F01D5/147 ,  F01D5/188 ,  F01D5/189 ,  F01D5/282 ,  F01D5/284 ,  F01D25/005 ,  F01D25/12 ,  F01D25/14 ,  F05D2240/12 ,  F05D2240/128 ,  F05D2240/14 ,  F05D2240/15 ,  F05D2240/301 ,  F05D2250/141 ,  F05D2250/231 ,  F05D2260/201 ,  F05D2300/2112 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/6033 ,  Y10T428/131 ,  Y10T428/1314 ,  Y10T428/24298 ,  Y10T428/24322 ,  Y10T428/24331 ,  Y10T428/24612 ,  Y10T428/24744

Abstract: A ceramic matrix composite article, method for forming the article, and perforated ply which may be incorporated therein are disclosed. The article includes at least one shell ply forming an exterior wall having first and second portions and defining a plenum. An annular brace formed of at least one structural support ply is disposed within the plenum, including a first integral portion integral with and part of the first portion of the exterior wall, a first curved portion extending from the first integral portion and curving across the article plenum to the second portion of the exterior wall, a second integral portion integral with and part of the second portion of the exterior wall, a second curved portion extending from the second integral portion and curving across the article plenum to the first curved portion, and an overlap in which the first and second curved portions are integral.

公开(公告)号：US20180363475A1

公开(公告)日：2018-12-20

申请号：US15624893

申请日：2017-06-16

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Peter de DIEGO ,  Jacob John KITTLESON

IPC: F01D5/28 ,  F01D5/14 ,  C04B35/71 ,  C04B35/622

CPC classification number: F01D5/282 ,  C04B35/622 ,  C04B35/71 ,  F01D5/147 ,  F01D5/284 ,  F05D2230/31 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2300/6033 ,  F05D2300/6034

Abstract: A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.