公开(公告)号：US11231044B2

公开(公告)日：2022-01-25

申请号：US16176250

申请日：2018-10-31

Applicant: Rolls-Royce Corporation

Inventor： Bronwyn Power

IPC: F04D29/32 ,  F01D5/14 ,  F04D29/54

Abstract: An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship 0.4

公开(公告)号：US11220928B1

公开(公告)日：2022-01-11

申请号：US17000905

申请日：2020-08-24

Applicant: Rolls-Royce Corporation

Inventor： Alexandra Baucco ,  Aaron D. Sippel ,  Ted J. Freeman

IPC: F01D25/12 ,  F02C7/12

Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

公开(公告)号：US20220002857A1

公开(公告)日：2022-01-06

申请号：US17360375

申请日：2021-06-28

Applicant: Rolls-Royce Corporation

Inventor： Li Li ,  Taylor K. Blair ,  Stephanie Gong

IPC: C23C4/18 ,  C23C4/02

Abstract: In one example, a method for forming a coating system including a bond coat and an environmental barrier coating on a ceramic or CMC substrate, e.g., with an abradable coating on the environmental barrier coating. The method may include depositing a bond coat on a ceramic or ceramic matrix composite (CMC) substrate to form an as-deposited bond coat; heat treating the as-deposited bond coat following the deposition of the as-deposited bond coat on the substrate to form a heat treated bond coat; depositing an environment barrier coating (EBC) layer on the heat treated bond coat to form as deposited EBC layer; and heat treating the as-deposited EBC layer to form a heat treated EBC layer.

公开(公告)号：US11215080B1

公开(公告)日：2022-01-04

申请号：US16951582

申请日：2020-11-18

Applicant: Rolls-Royce Corporation

Inventor： Ted J. Freeman ,  Aaron D. Sippel

IPC: F01D11/08 ,  F01D25/12 ,  F01D25/24 ,  F01D25/28

Abstract: A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The carrier assembly includes a forward carrier segment and an aft carrier segment, and each of the forward carrier segment and aft carrier segment include integrated pins. The carrier assembly is configured to couple the blade track segment to the turbine outer case.

公开(公告)号：US20210404050A1

公开(公告)日：2021-12-30

申请号：US17167662

申请日：2021-02-04

Applicant: Rolls-Royce Corporation

Inventor： Kang N. Lee ,  Matthew R. Gold

IPC: C23C14/32 ,  C04B41/89 ,  F01D5/28 ,  C04B41/00 ,  C04B41/52 ,  C23C4/11 ,  C23C4/134 ,  C23C14/08 ,  C23C14/10 ,  C23C14/54 ,  H01J37/32

Abstract: An article may include a substrate defining at least one at least partially obstructed surface. The substrate includes at least one of a ceramic or a ceramic matrix composite. The article also may include a multilayer, multi-microstructure environmental barrier coating on the at least partially obstructed substrate. The multilayer, multi-microstructure environmental barrier coating includes a first layer comprising a rare earth disilicate and a substantially dense microstructure; and a second layer on the first layer. The second layer includes a columnar microstructure and at least one of a rare earth monosilicate or a thermal barrier coating composition comprising a base oxide comprising zirconia or hafnia; a primary dopant comprising ytterbia; a first co-dopant comprising samaria; and a second co-dopant comprising at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia.

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：US20210388767A1

公开(公告)日：2021-12-16

申请号：US17317357

申请日：2021-05-11

Applicant: Rolls-Royce Corporation

Inventor： Scott Nelson ,  Quinlan Y. Shuck ,  Ted J. Freeman ,  Timothy Fuesting ,  Jonathan McCrory

IPC: F02C7/24 ,  F01D25/14

Abstract: A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.

公开(公告)号：US11199097B2

公开(公告)日：2021-12-14

申请号：US16773419

申请日：2020-01-27

Applicant: Rolls-Royce Corporation

Inventor： Bruce Edward Varney

IPC: F01D5/18 ,  F01D25/08 ,  F01D9/06

Abstract: A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 μm).

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.