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公开(公告)号：US10731252B2
公开(公告)日：2020-08-04
申请号：US15989697
申请日：2018-05-25
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Stephen Harris
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.
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公开(公告)号：US20190301292A1
公开(公告)日：2019-10-03
申请号：US15944095
申请日：2018-04-03
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Stephen Harris
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.
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公开(公告)号：US20180312442A1
公开(公告)日：2018-11-01
申请号：US15967664
申请日：2018-05-01
Inventor： Robert Shinavski , Joseph Doyle , Andrew Ritchey , Stephen Harris
IPC: C04B35/80 , C04B35/628 , C04B35/657
Abstract: A ceramic matrix composite (CMC) is formed by infiltrating a metal or alloy into a fiber preform in a reactor or furnace that is separated into multiple discrete temperature zones. The gradual cooling of the CMC is controlled, such that upon solidification, a narrow, planar, solidification front is created which allows the expanding metal or alloy to move into a hotter section of the fiber preform, opposed to the surface of the CMC. A discrete solidification front is established that moves through the ceramic matrix composite (CMC) as the composite cools.
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公开(公告)号：US11760699B2
公开(公告)日：2023-09-19
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
CPC classification number: C04B41/5183 , C04B41/0081 , C04B41/4523 , C04B41/5066 , C04B41/87 , C04B2235/3873 , C04B2235/616
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.
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公开(公告)号：US11746660B2
公开(公告)日：2023-09-05
申请号：US17557027
申请日：2021-12-20
Inventor： Michael J. Whittle , Stephen Harris
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.
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Patent Agency Ranking
公开(公告)号：US20230193763A1
公开(公告)日：2023-06-22
申请号：US17557027
申请日：2021-12-20
Inventor： Michael J. Whittle, JR. , Stephen Harris
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.
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公开(公告)号：US10822280B2
公开(公告)日：2020-11-03
申请号：US16116173
申请日：2018-08-29
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Stephen Harris , David Smolenski
IPC: C04B35/80 , C04B35/628 , C04B35/634 , C04B35/638 , C04B35/657 , C04B37/00 , B29C70/00 , B29C48/00 , B29C48/08 , B29B11/00 , B32B37/15 , B32B38/00 , C08J5/12 , B32B5/02 , B32B9/00 , C08J5/24 , B32B37/20
Abstract: A method of making a fiber preform for ceramic matrix composite (CMC) fabrication comprises laminating an arrangement of fibers between polymer sheets comprising an organic polymer, which may function as a fugitive binder during fabrication, to form a flexible prepreg sheet. A plurality of the flexible prepreg sheets are laid up in a predetermined geometry to form a stack, and the stack is heated to soften the organic polymer and bond together the flexible prepreg sheets into a bonded prepreg structure. Upon cooling of the bonded prepreg structure, a rigid preform is formed. The rigid preform is heated at a sufficient temperature to pyrolyze the organic polymer. Thus, a porous preform that may undergo further processing into a CMC is formed.
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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
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.
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公开(公告)号：US11773730B2
公开(公告)日：2023-10-03
申请号：US17508314
申请日：2021-10-22
Inventor： Michael J. Whittle , Steven Hillier , Stephen Harris , Sungbo Shim
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.
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公开(公告)号：US20230130393A1
公开(公告)日：2023-04-27
申请号：US17508314
申请日：2021-10-22
Inventor： Michael J. Whittle , Steven Hillier , Stephen Harris , Sungbo Shim
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.
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