公开(公告)号：US11339714B2

公开(公告)日：2022-05-24

申请号：US17061057

申请日：2020-10-01

Applicant: ROLLS-ROYCE plc ,  ROLLS-ROYCE CORPORATION

Inventor： Rory D Stieger ,  Daniel Swain

IPC: F02C3/08 ,  F02C7/18

Abstract: A gas turbine engine comprises, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a free power turbine. The gas-generator compressor is an axi-centrifugal compressor comprising a plurality of axial compression stages followed by a single centrifugal compression stage, wherein the International Standard Atmosphere, sea-level static (hereinafter ISA SLS) design point pressure ratio of the axi-centrifugal compressor is from 12 to 16, and a ratio of the ISA SLS pressure rise across the axial compression stages to the ISA SLS pressure rise across the centrifugal compression stage is from 0.75 to 1.

公开(公告)号：US20220154582A1

公开(公告)日：2022-05-19

申请号：US17592226

申请日：2022-02-03

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

Inventor： Michael J. Whittle ,  Louise J. Gale ,  Stephan J. Pattison ,  Anthony G. Razzell ,  Ian M. Edmonds ,  Michael G. Abbott

IPC: F01D5/28 ,  F01D5/14 ,  F01D9/04

Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

公开(公告)号：US11336151B2

公开(公告)日：2022-05-17

申请号：US16404396

申请日：2019-05-06

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： David Scothern ,  Mark Boden ,  Don Klemen ,  William Williamson ,  Brian Maners

IPC: H02K9/19 ,  H02K5/173 ,  H02K5/20

Abstract: An electric starter-generator is described. The generator may comprise a rotor, a housing, two bearings, a stator, and a cooling-fluid flowpath. The cooling-fluid flowpath may comprise a cooling-fluid entrance and exit, and a cooling-fluid channel in fluid communication with the entrance and exit. At least a portion of the channel may be defined by a fluid-tight coupling of the housing and a sleeve radially surrounding the outer race of either the bearings. The portion may form an annulus about the axis. The portion may comprise a radially inner surface defined by the sleeve, a radially outer surface define by said housing, and two axial surfaces. The two axial surfaces may extend a distance from the radially inner to outer surfaces that is less than a distance from one of the two axial surfaces to the other of the two axial surfaces.

公开(公告)号：US11300008B2

公开(公告)日：2022-04-12

申请号：US16591388

申请日：2019-10-02

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

Inventor： Kerry J. Lighty ,  Phillip Burnside

IPC: F01D25/18 ,  F16H57/04 ,  F01D25/16 ,  F16C17/02 ,  F16C33/10

Abstract: A lubricant scavenging system for a turbine engine having a pair of concentric, counter-rotating shafts. The system comprises a lubricant sump housing having a radially inner surface, a pair of pedestal mounts each adapted to receive a bearing assembly from a respective shaft, a lubricant collection point axially disposed between the pedestal mounts, and a pair of axial channels adapted to guide lubricant toward the lubricant collection point.

公开(公告)号：US20210403389A1

公开(公告)日：2021-12-30

申请号：US17166273

申请日：2021-02-03

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

Inventor： Sungbo Shim ,  Kang N. Lee ,  Stephen Isaiah Harris ,  Andrew Joseph Lazur

IPC: C04B37/00 ,  C23C28/00 ,  F01D5/28 ,  C04B41/89 ,  C23C20/04 ,  C04B41/00 ,  C04B41/85 ,  C04B41/45 ,  C04B41/50 ,  C04B41/52

Abstract: In some examples, a method may include depositing, from a slurry comprising particles including silicon metal, a bond coat precursor layer including the particles comprising silicon metal directly on a ceramic matrix composite substrate. The method also may include locally heating the bond coat precursor layer to form a bond coat comprising silicon metal. Additionally, the method may include forming a protective coating on the bond coat. In some examples, an article may include a ceramic matrix composite substrate, a bond coat directly on the substrate, and a protective coating on the bond coat. The bond coat may include silicon metal and a metal comprising at least one of Zr, Y, Yb, Hf, Ti, Al, Cr, Mo, Nb, Ta, or a rare earth metal.

公开(公告)号：US11198276B2

公开(公告)日：2021-12-14

申请号：US16277189

申请日：2019-02-15

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

Inventor： Sungbo Shim ,  Benjamin Lai

IPC: B32B18/00 ,  C04B35/626 ,  C04B35/628 ,  C04B35/573 ,  C04B35/80

Abstract: A method of forming a ceramic matrix composite (CMC) component having an engineered surface includes applying a surface slurry comprising first particulate solids in a liquid carrier to an outer surface of a ceramic fiber preform. The surface slurry is dried to remove the liquid carrier, and thus a surface slurry layer comprising the first particulate solids is formed on the outer surface. The surface slurry layer is polished to a predetermined thickness and/or surface finish. After polishing, a ceramic tape comprising second particulate solids is applied to the surface slurry layer, and pressure is applied to attach the ceramic tape to the surface slurry layer and to induce consolidation of the ceramic tape and the surface slurry layer. Thus, a multilayer surface region comprising the surface slurry layer and a ceramic tape layer is formed on the ceramic fiber preform. The ceramic fiber preform and the multilayer surface region are infiltrated with a molten material, and, upon cooling, a CMC component having an engineered surface is formed.

公开(公告)号：US11196320B2

公开(公告)日：2021-12-07

申请号：US16690510

申请日：2019-11-21

Applicant: Rolls-Royce plc ,  Rolls-Royce Corporation

Inventor： Mark Boden ,  Donald Klemen ,  Jonathan Terrell ,  Brian Maners

IPC: H02K5/15 ,  H02K7/00 ,  H02K5/22 ,  H02K1/27

Abstract: A rotor of an electric machine includes a main rotor body having a longitudinal axis, the main rotor body comprising: a hollow cylinder body with a first end and a second end; an integral end flange at the first end; a separate end flange disposed at the second end of the cylinder body; and laminations disposed on an outer surface of the cylinder body, the laminations comprising magnetic material.

公开(公告)号：US11187098B2

公开(公告)日：2021-11-30

申请号：US16723249

申请日：2019-12-20

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

Inventor： David J. Thomas ,  Jeffrey A. Walston ,  Aaron D. Sippel ,  Daniel K. Vetters ,  Alexandra Baucco ,  Jeffrey M. Crutchfield

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

Abstract: An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a supported component, illustratively used as a heat shield. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

公开(公告)号：US20210340875A1

公开(公告)日：2021-11-04

申请号：US17376632

申请日：2021-07-15

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Sven SCHRAPE ,  Bernhard MÜCK ,  Jens NIPKAU ,  Thomas GIERSCH ,  Frank HEINICHEN ,  John DODDS

IPC: F01D5/14

Abstract: A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N≥2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.

公开(公告)号：US11162377B2

公开(公告)日：2021-11-02

申请号：US16428319

申请日：2019-05-31

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

Inventor： Robert J. Shinavski ,  Thomas Tran ,  Kevin Lukhard ,  Ted J. Freeman ,  Steffan Brown

IPC: F01D9/04 ,  F01D5/28 ,  F01D25/00

Abstract: A turbine vane comprising ceramic matrix composite materials. The turbine vane includes an vane support core, an airfoil, and a pair of end walls that are spaced apart from one another to define a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.