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：US11286792B2

公开(公告)日：2022-03-29

申请号：US16526274

申请日：2019-07-30

Applicant: Rolls-Royce plc

Inventor： Anthony Razzell ,  Michael J. Whittle ,  Ian M. Edmonds

IPC: F01D5/18 ,  C04B35/80 ,  F01D5/28

Abstract: An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.

公开(公告)号：US20230094750A1

公开(公告)日：2023-03-30

申请号：US17491487

申请日：2021-09-30

Applicant: Rolls-Royce plc

Inventor： Ian M. Edmonds ,  Anthony G. Razzell

IPC: C04B35/80 ,  F01D9/04 ,  C04B35/628

Abstract: A method of forming a ceramic matrix composite component. The ceramic matrix composite component is adapted for use in a gas turbine engine. The method including forming the component using ceramic materials and infiltrating the component with a matrix material.

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.

公开(公告)号：US11434177B2

公开(公告)日：2022-09-06

申请号：US16410404

申请日：2019-05-13

Applicant: Rolls-Royce plc

Inventor： Anthony G. Razzell ,  Michael J. Whittle ,  Ian M. Edmonds

IPC: C04B41/45 ,  C04B35/565 ,  C04B41/50 ,  C04B41/87

Abstract: A component for use in a gas turbine engine is made from ceramic materials. The component is made from a core preform containing ceramic reinforcement fibers. A plurality of preform tows are applied on at least a portion of the core preform and extend along at least a portion of the core preform to provide an outermost surface. The core preform and the plurality of preform tows are infiltrated with ceramic matrix material to form a ceramic matrix composite component.

公开(公告)号：US11255200B2

公开(公告)日：2022-02-22

申请号：US16774793

申请日：2020-01-28

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 ,  C04B35/64

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：US11149553B2

公开(公告)日：2021-10-19

申请号：US16530604

申请日：2019-08-02

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Ian M. Edmonds

IPC: F01D5/14 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12

Abstract: An airfoil assembly for use in a turbine of a gas turbine engine includes an airfoil that extends radially relative to an axis. The airfoil includes an inner surface that defines a cooling cavity that extends radially into the airfoil and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a section side of the airfoil. The airfoil assembly further includes features for increasing the heat transfer coefficient of the airfoil.

公开(公告)号：US20210032995A1

公开(公告)日：2021-02-04

申请号：US16526274

申请日：2019-07-30

Applicant: Rolls-Royce plc

Inventor： Anthony Razzell ,  Michael J. Whittle ,  Ian M. Edmonds

IPC: F01D5/18 ,  C04B35/80

Abstract: An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a plurality of cooling passages that extend from the cooling cavity through the airfoil.

公开(公告)号：US11933195B2

公开(公告)日：2024-03-19

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 ,  C04B35/64 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D5/284 ,  F01D5/141 ,  F01D5/282 ,  F01D9/041 ,  C04B35/64 ,  F01D5/288 ,  F05D2240/12 ,  F05D2260/941 ,  F05D2300/6033

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.