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：US10370997B2

公开(公告)日：2019-08-06

申请号：US14721651

申请日：2015-05-26

Applicant: ROLLS-ROYCE CORPORATION ,  ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC. ,  ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.

Inventor： Daniel Kent Vetters ,  David J. Thomas ,  Douglas David Dierksmeier ,  Jun Shi ,  Todd Engel

IPC: F01D11/12 ,  F01D25/24 ,  F01D9/02

Abstract: A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.

公开(公告)号：US10227696B2

公开(公告)日：2019-03-12

申请号：US15677378

申请日：2017-08-15

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

Inventor： Chong M. Cha ,  David Liliedahl ,  Richard Kidd ,  Ross Galligher ,  Nicholas Doan

IPC: C23C16/455 ,  C23C16/04 ,  C23C16/44 ,  C23C16/458 ,  C23C16/46 ,  C23C16/52 ,  C23C16/24 ,  F01D5/28

Abstract: A method includes heating, using a heat source, a reactor vessel including a substrate in a radially central core region of the reactor vessel and introducing, using at least one reactor inlet in an outer wall of the reactor vessel, a precursor gas to the reactor vessel. The at least one reactor inlet is configured to swirling flow of the precursor gas around the radially central core region of the reactor vessel. The material deposits on the substrate from the precursor gas. The method includes removing, using at least one reactor outlet, an exhaust gas from the reactor vessel.

公开(公告)号：US10221713B2

公开(公告)日：2019-03-05

申请号：US14721590

申请日：2015-05-26

Applicant: ROLLS-ROYCE CORPORATION ,  ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC. ,  ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.

Inventor： Daniel Kent Vetters ,  David J. Thomas ,  Ted Freeman ,  Joseph Lamusga ,  Rick Uskert

IPC: F01D11/02 ,  F01D9/04 ,  F01D25/24

Abstract: A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.

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：US20180370863A1

公开(公告)日：2018-12-27

申请号：US16014660

申请日：2018-06-21

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

Inventor： Li Li ,  Sungbo Shim ,  Sunny Chang

IPC: C04B41/52 ,  C23C4/12 ,  C23C4/04 ,  B01J20/30

Abstract: A method of forming an impurity barrier layer on a CMC substrate may include introducing, to a heated plume of a thermal spray gun, a composite feedstock that includes a first coating material including a plurality of first particles; and a second coating material that may be different from the first coating material, where the second coating material at least partially encapsulates at least a portion of respective surfaces of the plurality of first particles; and directing, using the heated plume, at least the first coating material to a surface of a CMC substrate to deposit an impurity barrier layer including at least the first coating material.

公开(公告)号：US10138168B2

公开(公告)日：2018-11-27

申请号：US15404424

申请日：2017-01-12

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Sungbo Shim

IPC: B05D1/18 ,  C04B35/80 ,  C04B35/657 ,  C04B35/628 ,  B05D1/02 ,  B05D1/28 ,  F23R3/00 ,  F01D5/28 ,  F01D9/02 ,  F01D11/00 ,  C04B35/573

Abstract: A method of melt infiltration for producing a ceramic matrix composite comprises applying a non-wetting coating onto one or more outer surfaces of a porous fiber preform. The non-wetting coating comprises a non-wetting material with which molten silicon has a contact angle of at least about 45°. After applying the non-wetting coating, an uncoated portion of the porous fiber preform is immersed into a molten material comprising silicon, and the molten material is infiltrated into the porous fiber preform through the uncoated portion. The non-wetting coating serves as a barrier to inhibit or prevent the molten material from penetrating the one or more outer surfaces. After infiltration of the molten material into the porous fiber preform, the molten material is cooled to form a ceramic matrix composite, and the non-wetting coating is removed.

公开(公告)号：US10087770B2

公开(公告)日：2018-10-02

申请号：US14721620

申请日：2015-05-26

Applicant: ROLLS-ROYCE CORPORATION ,  ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC. ,  ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.

Inventor： Daniel Kent Vetters ,  David J. Thomas ,  Ted Freeman ,  Douglas David Dierksmeier ,  Jun Shi ,  Todd Engel

IPC: F01D11/08 ,  F01D25/00 ,  F01D25/24 ,  F01D9/04

Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.

公开(公告)号：US10060294B2

公开(公告)日：2018-08-28

申请号：US15130253

申请日：2016-04-15

Applicant: Rolls-Royce High Temperature Composites, Inc.

Inventor： Joseph P. Lamusga

IPC: F01D11/08 ,  F01D25/28 ,  F01D25/00 ,  F01D9/02

CPC classification number: F01D25/28 ,  F01D9/02 ,  F01D11/08 ,  F01D11/14 ,  F01D25/005 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2250/184 ,  F05D2300/6033 ,  Y02T50/672

Abstract: An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position.

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.