公开(公告)号：US20230193782A1

公开(公告)日：2023-06-22

申请号：US17557026

申请日：2021-12-20

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

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

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

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

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：US11560799B1

公开(公告)日：2023-01-24

申请号：US17508342

申请日：2021-10-22

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

Inventor： Stephen Harris ,  Michael J. Whittle

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

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

公开(公告)号：US11117838B2

公开(公告)日：2021-09-14

申请号：US15987269

申请日：2018-05-23

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Wayne Steffier ,  Michael Jacquinto ,  Stephen Harris ,  Robert Shinavski ,  Todd Engel

IPC: C04B35/80 ,  C04B35/634 ,  C04B35/638 ,  C04B35/657 ,  C04B35/628

Abstract: A method of making a fiber preform for ceramic matrix composite (CMC) fabrication that utilizes a fugitive binder and a machining step is described. The method includes, according to one embodiment, laying up a plurality of plies to form a stack, where each ply comprises an arrangement of fibers. The stack is infiltrated with a polymer at an elevated temperature to form an infiltrated stack that is cooled to form a rigid preform. The rigid fiber preform is machined to have a predetermined shape, such that a machined fiber preform is formed. A composite assembly including the machined fiber preform is formed and then the composite assembly is heated at a sufficient temperature to pyrolyze the polymer. Thus, a porous preform of a predetermined geometry is formed for further processing into a CMC.

公开(公告)号：US20210009480A1

公开(公告)日：2021-01-14

申请号：US16924742

申请日：2020-07-09

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Christopher Whitmore ,  Stephen Harris ,  Sungbo Shim ,  Timothy Western

IPC: C04B41/51 ,  C04B41/87 ,  C04B41/45 ,  C04B41/00

Abstract: A method of altering a surface of a ceramic matrix composite to aid in nodule removal is described. A fiber preform comprising a framework of ceramic fibers is heated to a temperature at or above a melting temperature of silicon. During the heating, the fiber preform is infiltrated with a molten material comprising silicon. After the infiltration, the fiber preform is cooled, and the infiltrated fiber preform is exposed to a gas comprising nitrogen during cooling. Silicon nitride may be formed by a reaction of free (unreacted) silicon at or near the surface of the infiltrated fiber preform with the nitrogen. Thus, a ceramic matrix composite having a surface configured for easy nodule removal is formed. Any silicon nodules formed on the surface during cooling may be removed without machining or heat treatment.

公开(公告)号：US10767498B2

公开(公告)日：2020-09-08

申请号：US15944095

申请日：2018-04-03

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Stephen Harris

IPC: F01D5/30 ,  F01D5/28 ,  F01D5/14

Abstract: A blade assembly for use in a gas turbine engine. The blade assembly includes a blade, a platform distinct from the blade and configured to extend around the blade, and a pin that couples the platform with the blade.

公开(公告)号：US10577961B2

公开(公告)日：2020-03-03

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: F01D5/28 ,  F01D5/22 ,  F01D11/00

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：US20190367417A1

公开(公告)日：2019-12-05

申请号：US15995537

申请日：2018-06-01

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Stephen Harris

IPC: C04B35/80 ,  C04B35/565 ,  F01D5/28

Abstract: A method of controllably coating a fiber preform has been developed. The method includes infiltrating a fiber preform with a first solvent to form a solvent-filled preform. After the infiltration, a slurry is applied to one or more outer surfaces of the solvent-filled preform to form a slurry coating thereon. The slurry coating comprises particulate solids dispersed in a second solvent having a vapor pressure higher than that of the first solvent. The slurry coating and the solvent-filled preform are dried. During drying, the second solvent evaporates from the slurry coating before the first solvent evaporates from the solvent-filled preform. The slurry coating dries to form a porous surface coating comprising the particulate solids on the one or more outer surfaces of the solvent-filled preform. The drying of the solvent-filled preform continues after formation of the porous surface coating to remove the first solvent.

公开(公告)号：US20190360097A1

公开(公告)日：2019-11-28

申请号：US15989697

申请日：2018-05-25

Applicant: Rolls-Royce High Temperature Composites Inc.

Inventor： Stephen Harris

IPC: C23C16/455 ,  C04B41/85 ,  C04B41/87 ,  C04B41/45 ,  C23C16/32 ,  C23C16/34 ,  C23C16/26

Abstract: An apparatus for coating specimens includes a reaction chamber and a plurality of reaction modules in the reaction chamber for containing specimens to be coated, where each reaction module includes a module inlet and a module outlet. A plurality of conduits are configured to be in fluid communication with at least one gas source external to the reaction chamber, and each of the conduits terminates in one of the reaction modules for delivery of gaseous reagents to the specimens to be coated. The module outlets are in fluid communication with the reaction chamber for expulsion of gaseous reaction products from the reaction modules.