公开(公告)号：US11746660B2

公开(公告)日：2023-09-05

申请号：US17557027

申请日：2021-12-20

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

Inventor： Michael J. Whittle ,  Stephen Harris

IPC: F01D5/18 ,  F01D5/28 ,  F01D5/14

CPC classification number: F01D5/18 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F05D2250/75 ,  F05D2260/231 ,  F05D2300/6033 ,  F05D2300/612

Abstract: An airfoil assembly for a gas turbine engine includes an airfoil extending radially relative to a central reference axis. A spar is located within the airfoil and spaced from the airfoil at all radial locations along the airfoil such that a gap is maintained between the airfoil and the spar. A foam is located between the airfoil and the spar.

公开(公告)号：US20230193763A1

公开(公告)日：2023-06-22

申请号：US17557027

申请日：2021-12-20

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

Inventor： Michael J. Whittle, JR. ,  Stephen Harris

IPC: F01D5/18 ,  F01D5/28 ,  F01D5/14

CPC classification number: F01D5/18 ,  F01D5/284 ,  F01D5/147 ,  F01D5/282 ,  F05D2250/75 ,  F05D2260/231 ,  F05D2300/6033 ,  F05D2300/612

Abstract: An airfoil assembly for a gas turbine engine includes an airfoil extending radially relative to a central reference axis. A spar is located within the airfoil and spaced from the airfoil at all radial locations along the airfoil such that a gap is maintained between the airfoil and the spar. A foam is located between the airfoil and the spar.

公开(公告)号：US20190323371A1

公开(公告)日：2019-10-24

申请号：US15959906

申请日：2018-04-23

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

Inventor： Stephen Harris ,  Aaron D. Sippel ,  Ted J. Freeman ,  Anthony Razzell

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

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each fit within slots formed in the rotor disk to couple the blades to the rotor disk. Platform segments are arranged about each of the blades.

公开(公告)号：US11834956B2

公开(公告)日：2023-12-05

申请号：US17557026

申请日：2021-12-20

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

Inventor： Michael J. Whittle ,  Stephen Harris

IPC: F01D25/14 ,  F01D11/08 ,  F01D5/28 ,  F01D5/14 ,  F01D5/18

CPC classification number: F01D25/145 ,  F01D5/147 ,  F01D5/18 ,  F01D5/28 ,  F01D11/08 ,  F05D2240/11 ,  F05D2260/231 ,  F05D2300/612

Abstract: A turbine shroud assembly for a gas turbine engine includes a shroud wall extending circumferentially partway around a central reference axis to define a gas path of the gas turbine engine. An attachment feature extends radially from the shroud wall. A foam is located at least on the shroud wall.

公开(公告)号：US11504813B2

公开(公告)日：2022-11-22

申请号：US16876834

申请日：2020-05-18

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

Inventor： Michael J. Whittle ,  Stephen Harris ,  Keith Sadler ,  Matthew D. Thomason ,  Andrew Norton ,  James Kell

IPC: B23P6/00 ,  F01D5/00 ,  F01D5/28 ,  G01M15/14

Abstract: A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.

公开(公告)号：US20210354253A1

公开(公告)日：2021-11-18

申请号：US16876834

申请日：2020-05-18

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

Inventor： Michael J. Whittle ,  Stephen Harris ,  Keith Sadler ,  Matthew D. Thomason ,  Andrew Norton ,  James Kell

IPC: B23P6/00 ,  G01M15/14 ,  F01D5/00 ,  F01D5/28

Abstract: A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.

公开(公告)号：US11773730B2

公开(公告)日：2023-10-03

申请号：US17508314

申请日：2021-10-22

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

Inventor： Michael J. Whittle ,  Steven Hillier ,  Stephen Harris ,  Sungbo Shim

IPC: F01D5/18 ,  C04B35/80 ,  C04B41/45 ,  F01D5/14 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D5/187 ,  C04B35/80 ,  C04B41/457 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F01D9/041 ,  C04B2235/616 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2260/2212 ,  F05D2260/232 ,  F05D2300/6033

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.

公开(公告)号：US20230130393A1

公开(公告)日：2023-04-27

申请号：US17508314

申请日：2021-10-22

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

Inventor： Michael J. Whittle ,  Steven Hillier ,  Stephen Harris ,  Sungbo Shim

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28 ,  F01D9/04

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.

公开(公告)号：US11536205B2

公开(公告)日：2022-12-27

申请号：US16835942

申请日：2020-03-31

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Ian M. Edmonds ,  Stephen Harris

IPC: F02C9/00 ,  F02C7/12 ,  F01D21/00 ,  F01D5/28 ,  F02C9/54

Abstract: A gas turbine engine system includes an engine component comprising ceramic matrix composite materials, at least one control system configured to control at least a temperature of the engine component, and a controller. The controller includes a degradation map stored therein. The degradation map includes degradation fields, each field defined by a unique range of temperatures and stresses of the component and correlated to different types of degradation of the component. The controller is configured to determine a first temperature and stress of the component and a first field based on the first temperature and stress, determine a second field different from the first and a second temperature and stress that would locate the component in the second field, and instruct the control system to change the temperature of the component from the first to the second temperature to locate the component in the second field.

公开(公告)号：US20210301737A1

公开(公告)日：2021-09-30

申请号：US16835942

申请日：2020-03-31

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Ian M. Edmonds ,  Stephen Harris

IPC: F02C9/54 ,  F02C7/12

Abstract: A gas turbine engine system includes an engine component comprising ceramic matrix composite materials, at least one control system configured to control at least a temperature of the engine component, and a controller. The controller includes a degradation map stored therein. The degradation map includes degradation fields, each field defined by a unique range of temperatures and stresses of the component and correlated to different types of degradation of the component. The controller is configured to determine a first temperature and stress of the component and a first field based on the first temperature and stress, determine a second field different from the first and a second temperature and stress that would locate the component in the second field, and instruct the control system to change the temperature of the component from the first to the second temperature to locate the component in the second field.