公开(公告)号：US20220097184A1

公开(公告)日：2022-03-31

申请号：US17444952

申请日：2021-08-12

Applicant: Rolls-Royce Corporation

Inventor： Joseph Peter Henderkott ,  Robert Frederick Proctor

IPC: B23P15/02 ,  F01D5/18 ,  B23P17/04 ,  B23P23/04 ,  F01D25/12

Abstract: An assembly for a dual-walled component of a gas turbine engine and methods of forming and repairing a dual-walled component. The assembly includes a cold section part having an outer surface that defines a plurality of impingement apertures, a hot section part including a pre-sintered preform, the hot section part positioned over the outer surface of the cold section part, and a plurality of support structures including the pre-sintered preform, the plurality of support structures positioned between the hot section part and the cold section part, the plurality of support structures separating the hot section part from the cold section part to define at least one cooling channel therebetween.

公开(公告)号：US11286798B2

公开(公告)日：2022-03-29

申请号：US16545791

申请日：2019-08-20

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

Inventor： Michael J. Whittle ,  Daniel K. Vetters ,  Ted J. Freeman ,  Eric Koenig ,  Jeff Crutchfield ,  Jeffrey A. Walston ,  David J. Thomas

IPC: F01D9/04 ,  F01D25/00

Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.

公开(公告)号：US11255265B2

公开(公告)日：2022-02-22

申请号：US16291681

申请日：2019-03-04

Applicant: Rolls-Royce Corporation

Inventor： John R. Gebhard

IPC: F02C7/06 ,  B01D45/14 ,  B01D19/00 ,  F01M13/04

Abstract: An air-oil separation system for a gas turbine engine system comprises a housing that extends circumferentially around an axis to define an interior chamber of the housing and a separation unit located in the chamber. The housing is formed to include an inlet configured to receive a mixture of air and oil, an oil outlet configured to conduct oil to exit the housing, and an air outlet configured to conduct air to exit the housing. The air-oil separation unit separates air from the oil.

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.