公开(公告)号：US20190301292A1

公开(公告)日：2019-10-03

申请号：US15944095

申请日：2018-04-03

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Stephen Harris

IPC: F01D5/30 ,  F01D5/28 ,  F01D5/14

Abstract: A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

公开(公告)号：US20190292916A1

公开(公告)日：2019-09-26

申请号：US15926585

申请日：2018-03-20

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

Inventor： Ted J. Freeman ,  Jeremy P. Roehm ,  Robert J. Shinavski

IPC: F01D5/14

Abstract: Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.

公开(公告)号：US10399911B2

公开(公告)日：2019-09-03

申请号：US15005790

申请日：2016-01-25

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

Inventor： Sungbo Shim ,  Robert Wesley Thibault ,  Robert Shinavski ,  Kang N. Lee

IPC: C04B41/45 ,  C04B41/81 ,  C04B41/52 ,  C04B41/89 ,  C04B41/85 ,  C04B41/50 ,  C04B35/573 ,  C04B35/80 ,  C04B41/00 ,  C04B35/626 ,  B33Y10/00

Abstract: The disclosure describes techniques for forming a surface layer of an article including a CMC using a cast. In some examples, the surface layer includes three-dimensional surface features, which may increase adhesion between the CMC and a coating on the CMC. In some examples, the surface layer may include excess material, with or without three-dimensional surface features, which is on the CMC. The excess material may be machined to remove some of the excess material and facilitate conforming the article to dimensional tolerances, e.g., for fitting the article to another component. The excess material may reduce a likelihood that the CMC (e.g., reinforcement material in the CMC) is damaged by the machining.

公开(公告)号：US10370998B2

公开(公告)日：2019-08-06

申请号：US14721684

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 ,  Todd Engel ,  Matt Brandt

IPC: F01D11/12 ,  F01D9/04 ,  F01D25/24

Abstract: A segmented turbine shroud for radially encasing a turbine in a gas turbine engine comprises a carrier comprising a flange; a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving bore; an elongated pin extending through the pin-receiving bore; a bushing surrounding the elongated pin within the bore; and a flexible mounting member, the flexible mounting member being connected to the bushing and the carrier flange to thereby flexibly mount the CMC seal segment to the carrier.

公开(公告)号：US20180363132A1

公开(公告)日：2018-12-20

申请号：US16003615

申请日：2018-06-08

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Richard W. Kidd ,  Robert Shinavski

IPC: C23C16/34 ,  C23C16/30 ,  D06M11/58 ,  D06M11/80 ,  F01D25/00

CPC classification number: C23C16/342 ,  C04B35/565 ,  C04B35/62863 ,  C04B35/62868 ,  C04B35/62884 ,  C04B35/62894 ,  C04B35/62897 ,  C04B35/806 ,  C04B2235/3826 ,  C04B2235/46 ,  C04B2235/465 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/616 ,  C23C16/308 ,  D06M11/58 ,  D06M11/80 ,  D06M2101/16 ,  F01D25/005 ,  F05D2300/6033

Abstract: A method of forming a moisture-tolerant coating on a silicon carbide fiber includes exposing a silicon carbide fiber to a gaseous N precursor comprising nitrogen at an elevated temperature, thereby introducing nitrogen into a surface region of the silicon carbide fiber, and exposing the silicon carbide fiber to a gaseous B precursor comprising boron at an elevated temperature, thereby introducing boron into the surface region of the silicon carbide fiber. Silicon-doped boron nitride is formed at the surface region of the silicon carbide fiber without exposing the silicon carbide fiber to a gaseous Si precursor comprising Si. Thus, a moisture-tolerant coating comprising the silicon-doped boron nitride is grown in-situ on the silicon carbide fiber.

公开(公告)号：US20180312442A1

公开(公告)日：2018-11-01

申请号：US15967664

申请日：2018-05-01

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

Inventor： Robert Shinavski ,  Joseph Doyle ,  Andrew Ritchey ,  Stephen Harris

IPC: C04B35/80 ,  C04B35/628 ,  C04B35/657

Abstract: A ceramic matrix composite (CMC) is formed by infiltrating a metal or alloy into a fiber preform in a reactor or furnace that is separated into multiple discrete temperature zones. The gradual cooling of the CMC is controlled, such that upon solidification, a narrow, planar, solidification front is created which allows the expanding metal or alloy to move into a hotter section of the fiber preform, opposed to the surface of the CMC. A discrete solidification front is established that moves through the ceramic matrix composite (CMC) as the composite cools.

公开(公告)号：US20180222807A1

公开(公告)日：2018-08-09

申请号：US15878970

申请日：2018-01-24

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

Inventor： Sungbo Shim ,  Robert Shinavski ,  Ann Bolcavage

IPC: C04B41/45 ,  C04B41/00 ,  C04B41/50 ,  C04B41/51 ,  C04B41/52 ,  C04B41/87 ,  C04B41/88 ,  C23C4/134 ,  C23C4/04 ,  B05D1/18 ,  B05D3/02 ,  C23C4/126

CPC classification number: C04B41/456 ,  B05D1/18 ,  B05D3/0254 ,  C04B41/009 ,  C04B41/4554 ,  C04B41/5001 ,  C04B41/5024 ,  C04B41/5059 ,  C04B41/5133 ,  C04B41/5138 ,  C04B41/52 ,  C04B41/87 ,  C04B41/88 ,  C04B41/89 ,  C23C4/04 ,  C23C4/126 ,  C23C4/134 ,  C23C4/18 ,  F01D5/288 ,  F05D2230/312 ,  F05D2230/90 ,  F05D2300/222 ,  F05D2300/6033 ,  C04B35/80 ,  C04B35/565 ,  C04B35/806 ,  C04B35/584 ,  C04B41/4527 ,  C04B41/4582 ,  C04B41/5096 ,  C04B41/4519 ,  C04B41/4535 ,  C04B41/455 ,  C04B41/4517 ,  C04B41/4558 ,  C04B41/522 ,  C04B41/4537 ,  C04B41/5031 ,  C04B41/5035 ,  C04B41/5023 ,  C04B41/5037 ,  C04B41/5045

Abstract: An example method may include applying a bond coat comprising silicon or a silicon alloy on a surface of a ceramic or ceramic matrix composite substrate, where the bond coat comprises a plurality of pores; infiltrating a precursor into at least some pores of the plurality of pores; and heat-treating the bond coat and the precursor, where after heat-treating a porosity of the bond coat is less than about 5 vol. %, and where after heat-treating, the bond coat is substantially free of continuous porosity extending through a thickness of the bond coat.

公开(公告)号：US10030541B2

公开(公告)日：2018-07-24

申请号：US14789284

申请日：2015-07-01

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

Inventor： Daniel K. Vetters ,  Todd Engel ,  Robert J. Shinavski

IPC: F01D25/24

Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.

公开(公告)号：US20170321567A1

公开(公告)日：2017-11-09

申请号：US15660143

申请日：2017-07-26

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

Inventor： Daniel K. Vetters ,  David J. Thomas ,  Ted Freeman ,  Joseph Lamusga ,  Rick Uskert ,  Douglas D. Dierksmeier ,  Jun Shi ,  Todd Engel ,  Matt Brandt

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

CPC classification number: F01D11/02 ,  F01D9/04 ,  F01D25/246 ,  F05D2300/6033

Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

公开(公告)号：US09630885B2

公开(公告)日：2017-04-25

申请号：US14864082

申请日：2015-09-24

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

Inventor： Anthony Martin Goetz ,  Robert Shinavski ,  Stephen Isaiah Harris ,  Sean E. Landwehr

IPC: B32B9/00 ,  C04B41/45 ,  C04B41/87 ,  C04B41/85 ,  C04B41/53 ,  C04B41/52 ,  C04B41/50 ,  C04B35/565 ,  C04B35/573 ,  C04B35/626 ,  C04B35/628 ,  C04B35/634 ,  C04B35/636

CPC classification number: C04B35/806 ,  C04B35/565 ,  C04B35/573 ,  C04B35/62281 ,  C04B35/624 ,  C04B35/6261 ,  C04B35/6263 ,  C04B35/6264 ,  C04B35/62857 ,  C04B35/6286 ,  C04B35/62863 ,  C04B35/62865 ,  C04B35/62868 ,  C04B35/62873 ,  C04B35/634 ,  C04B35/636 ,  C04B35/6365 ,  C04B35/65 ,  C04B35/657 ,  C04B41/4584 ,  C04B41/5059 ,  C04B41/5096 ,  C04B41/52 ,  C04B41/53 ,  C04B41/85 ,  C04B41/87 ,  C04B2235/3826 ,  C04B2235/428 ,  C04B2235/48 ,  C04B2235/5224 ,  C04B2235/5228 ,  C04B2235/5232 ,  C04B2235/5236 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2235/5436 ,  C04B2235/5481 ,  C04B2235/6023 ,  C04B2235/616 ,  C04B2235/656 ,  C04B2235/6581

Abstract: A method of forming a composite article includes impregnating an inorganic fiber preform with a slurry composition. The slurry composition includes a particulate, a solvent, and a pre-gellant material. Gelling of the pre-gellant material in the slurry composition is initiated to immobilize the particulate and yield a gelled article, and substantially all solvent is removed from the gelled article to form a green composite article. The green composite article is then infiltrated with a molten infiltrant to form the composite article.