公开(公告)号：US12215593B1

公开(公告)日：2025-02-04

申请号：US18678892

申请日：2024-05-30

Applicant: Rolls-Royce Corporation

Inventor： David J. Thomas ,  Aaron D. Sippel ,  Ted J. Freeman ,  Clark J. Snyder

IPC: F01D25/28 ,  F01D5/22 ,  F01D11/00

Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a seal assembly. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The seal assembly is configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.

公开(公告)号：US11885225B1

公开(公告)日：2024-01-30

申请号：US18101568

申请日：2023-01-25

Applicant: Rolls-Royce Corporation

Inventor： Ted J. Freeman ,  Aaron D. Sippel ,  David J. Thomas

IPC: F01D11/08 ,  F01D25/24

CPC classification number: F01D11/08 ,  F01D25/246 ,  F05D2240/11 ,  F05D2300/6033

Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a retainer. The carrier segment is formed to include an attachment-receiving space. The blade track segment includes a shroud wall and attachment flanges that extends radially outward from the shroud wall into the attachment-receiving space of the carrier segment. The retainer couples the blade track segment to the carrier segment.

公开(公告)号：US11746658B2

公开(公告)日：2023-09-05

申请号：US17075257

申请日：2020-10-20

Applicant: Rolls-Royce Corporation

Inventor： Ted J. Freeman ,  Aaron D. Sippel

IPC: F01D5/14 ,  F01D25/24 ,  F01D11/08

CPC classification number: F01D5/143 ,  F01D11/08 ,  F01D25/246 ,  F05D2230/64 ,  F05D2240/11 ,  F05D2260/36 ,  F05D2300/6033 ,  Y10T29/49323

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：US20220381152A1

公开(公告)日：2022-12-01

申请号：US17329897

申请日：2021-05-25

Applicant: Rolls-Royce Corporation

Inventor： Ted J. Freeman ,  Aaron D. Sippel ,  David J. Thomas

IPC: F01D9/04 ,  F01D25/00

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

公开(公告)号：US11466855B2

公开(公告)日：2022-10-11

申请号：US16851782

申请日：2020-04-17

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

Inventor： Ted J. Freeman ,  Aaron D. Sippel

IPC: F23R3/00 ,  F23R3/60

Abstract: A combustor adapted for use in a gas turbine engine includes a combustor shell comprising metallic materials. The combustor shell is formed to define an internal space. The combustor further includes a heat shield mounted to an axially aft surface of the combustor shell within the internal space and a combustor liner arranged to extend along inner surfaces of the combustor shell within the internal space. The combustor liner cooperates with the heat shield to define a combustor chamber.

公开(公告)号：US11319828B1

公开(公告)日：2022-05-03

申请号：US17351741

申请日：2021-06-18

Applicant: Rolls-Royce Corporation

Inventor： Ted J. Freeman ,  Aaron D. Sippel ,  David J. Thomas

IPC: F01D11/08

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.

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：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：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：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.