公开(公告)号：US10787917B2

公开(公告)日：2020-09-29

申请号：US15971356

申请日：2018-05-04

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Ted J. Freeman ,  Christopher Barrett

IPC: F01D5/30

Abstract: A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.

公开(公告)号：US10995040B2

公开(公告)日：2021-05-04

申请号：US15456628

申请日：2017-03-13

Applicant: Rolls-Royce High Temperature Composites, Inc.

Inventor： Joseph Lamusga ,  Christopher Barrett

IPC: C04B41/51 ,  C04B35/80 ,  C04B41/45 ,  C04B41/50 ,  F01D11/00 ,  C04B35/573 ,  F01D5/28

Abstract: A method for fabricating a ceramic matrix composite component having a deltoid region is provided. The method includes providing a porous ceramic preform. The porous ceramic preform includes a layer-to-layer weave of ceramic fibers that forms a modified layer-to-layer woven core and at least one 2-dimensional layer of ceramic fibers that is disposed adjacent to the modified layer-to-layer woven core. The porous ceramic preform is formed into a ceramic matrix composite body having the deltoid region such that the modified layer-to-layer woven core extends through the deltoid region.

公开(公告)号：US10954809B2

公开(公告)日：2021-03-23

申请号：US15989666

申请日：2018-05-25

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Aaron D. Sippel ,  Bruce E. Varney ,  Ted J. Freeman ,  Christopher Barrett

IPC: F01D11/08 ,  F01D25/00 ,  F01D25/24 ,  B23P15/00 ,  C23C16/32 ,  C23C16/04

Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

公开(公告)号：US20180311708A1

公开(公告)日：2018-11-01

申请号：US15967005

申请日：2018-04-30

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Christopher Barrett

IPC: B08B9/04 ,  C04B35/565 ,  C04B35/80

CPC classification number: B08B9/04 ,  C04B35/565 ,  C04B35/573 ,  C04B35/62868 ,  C04B35/62873 ,  C04B35/806 ,  C04B2235/3826 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/6028 ,  C04B2235/616 ,  F05D2300/6033

Abstract: A method of slurry infiltration and cleaning to fabricate a ceramic matrix composite (CMC) component with an internal cavity or bore comprises inserting a number of rods into a hollow portion of a porous fiber preform, thereby forming a rod arrangement substantially filling the hollow portion. Each of the rods has a low-friction surface comprising a coefficient of static friction of about 0.1 or less. The porous fiber preform is exposed to a slurry comprising particulate solids in a liquid carrier, and the slurry infiltrates the porous fiber preform. Some fraction of the particulate solids is deposited within interstices of the porous fiber preform to form an impregnated fiber preform, and another fraction of the particulate solids is deposited within the hollow portion as excess slurry. After slurry infiltration, the rods are withdrawn from the hollow portion, and at least some of the excess slurry is removed with the rods.

公开(公告)号：US10717116B2

公开(公告)日：2020-07-21

申请号：US15967005

申请日：2018-04-30

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Christopher Barrett

IPC: C04B35/565 ,  C04B35/573 ,  B08B9/04 ,  C04B35/80 ,  C04B35/628 ,  C04B35/00

Abstract: A method of slurry infiltration and cleaning to fabricate a ceramic matrix composite (CMC) component with an internal cavity or bore comprises inserting a number of rods into a hollow portion of a porous fiber preform, thereby forming a rod arrangement substantially filling the hollow portion. Each of the rods has a low-friction surface comprising a coefficient of static friction of about 0.1 or less. The porous fiber preform is exposed to a slurry comprising particulate solids in a liquid carrier, and the slurry infiltrates the porous fiber preform. Some fraction of the particulate solids is deposited within interstices of the porous fiber preform to form an impregnated fiber preform, and another fraction of the particulate solids is deposited within the hollow portion as excess slurry. After slurry infiltration, the rods are withdrawn from the hollow portion, and at least some of the excess slurry is removed with the rods.

公开(公告)号：US20190338657A1

公开(公告)日：2019-11-07

申请号：US15971356

申请日：2018-05-04

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Ted J. Freeman ,  Christopher Barrett

IPC: F01D5/30

Abstract: A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.

公开(公告)号：US20180371930A1

公开(公告)日：2018-12-27

申请号：US15989666

申请日：2018-05-25

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc.

Inventor： Aaron D. Sippel ,  Bruce E. Varney ,  Ted J. Freeman ,  Christopher Barrett

IPC: F01D11/08 ,  F01D25/00 ,  F01D25/24

Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

公开(公告)号：US20180230064A1

公开(公告)日：2018-08-16

申请号：US15456628

申请日：2017-03-13

Applicant: Rolls-Royce High Temperature Composites, Inc.

Inventor： Joseph Lamusga ,  Christopher Barrett

IPC: C04B41/51 ,  F01D11/00 ,  C04B41/45 ,  C04B35/80 ,  C04B41/50 ,  F01D5/28

CPC classification number: C04B41/515 ,  C04B35/573 ,  C04B35/80 ,  C04B35/806 ,  C04B41/4584 ,  C04B41/5096 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5236 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/5252 ,  C04B2235/5256 ,  C04B2235/5268 ,  F01D5/282 ,  F01D5/284 ,  F01D11/00 ,  F05D2240/11 ,  F05D2250/11 ,  F05D2250/23 ,  F05D2300/222 ,  F05D2300/6033 ,  F05D2300/6034 ,  F05D2300/614

Abstract: A method for fabricating a ceramic matrix composite component having a deltoid region is provided. The method includes providing a porous ceramic preform. The porous ceramic preform includes a layer-to-layer weave of ceramic fibers that forms a modified layer-to-layer woven core and at least one 2-dimensional layer of ceramic fibers that is disposed adjacent to the modified layer-to-layer woven core. The porous ceramic preform is formed into a ceramic matrix composite body having the deltoid region such that the modified layer-to-layer woven core extends through the deltoid region.