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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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93.发明公开公开(公告)号：US20230193775A1
公开(公告)日：2023-06-22
申请号：US17554819
申请日：2021-12-17
Inventor： Ted J. Freeman , Jeremy Roehm
CPC classification number: F01D11/122 , F01D25/005 , F01D25/28 , F01D25/24 , F05D2240/11 , F05D2250/75 , F05D2300/6033 , F05D2300/6111 , F05D2260/30
Abstract: A turbine shroud segment for use in a gas turbine engine includes a ceramic shroud segment formed to define a circumferentially extending channel that opens radially inwardly and a layer of abradable material that extends axially along a radial inner surface of the ceramic shroud segment to provide a flow path surface of the turbine shroud segment.
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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：US11519279B2
公开(公告)日：2022-12-06
申请号：US17501793
申请日：2021-10-14
Applicant: Rolls-Royce High Temperature Composites Inc. , Rolls-Royce North American Technologies Inc.
Inventor： Robert J. Shinavski , Thomas Tran , Kevin Lukhard , Ted J. Freeman , Steffan Brown
Abstract: A turbine vane comprising ceramic matrix composite materials includes a vane support core, an airfoil, and an end wall that at least partially defines a gas path. The turbine vane is formed from a plurality of ceramic plies or preforms that are infiltrated with ceramic matrix material to form a one-piece ceramic matrix composite turbine vane.
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Patent Agency Ranking
公开(公告)号：US11428107B2
公开(公告)日：2022-08-30
申请号：US16429909
申请日：2019-06-03
Inventor： Jun Shi , Steffan Brown
Abstract: A bladed disk preform system is provided. Multiple sheets are formed or provided. Each of the sheets may include multiple ceramic fibers. Slots may be cut in each of the sheets before or after forming. The slots extend from an outer edge of the sheets inward toward a center of the sheets. The sheets are stacked on top of each other to form a bladed disk preform. The bladed disk preform is porous. The bladed disk preform may include a plurality of blade portions extending outward from a root portion. Each of the slots is positioned between adjacent blade portions.
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公开(公告)号：US11351696B2
公开(公告)日：2022-06-07
申请号：US16278265
申请日：2019-02-18
Inventor： Scott Nelson , Quinlan Shuck , Sean Landwehr , Sungbo Shim
IPC: B28B1/00 , B33Y10/00 , B29C64/165 , B33Y40/00 , C04B35/622 , C04B35/628 , C04B35/657 , C04B35/571 , C04B35/573 , C04B35/58 , C04B35/591 , C04B35/80
Abstract: A system and method for forming a porous ceramic preform is provided. The method may include forming a stacked powder structure including a binder layer and a powder layer on the binder layer. The binder layer may be formed by depositing a binder with a spray nozzle on a substrate. The powder layer may be formed by depositing a powder on the binder layer. The porous ceramic preform may be formed by heating the stacked powder structure to pyrolyze the binder. The porous ceramic preform is configured to be infiltrated by a molten material. The substrate may comprise a ceramic fiber preform. After melt infiltration of the porous ceramic preform and the ceramic fiber preform, a densified ceramic feature having a predetermined geometry may be formed on a ceramic matrix composite (CMC) component.
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公开(公告)号：US20220055957A1
公开(公告)日：2022-02-24
申请号：US17405273
申请日：2021-08-18
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Sungbo Shim , Richard Kidd , Kelly Kranjc , Robert Shinavski
Abstract: A method of making a ceramic matrix composite that exhibits chemical resistance has been developed. The method comprises depositing a compliant layer comprising boron nitride, silicon-doped boron nitride, and/or pyrolytic carbon on silicon carbide fibers, depositing a barrier layer having a high contact angle with molten silicon on the compliant layer, and depositing a wetting layer comprising silicon carbide, boron carbide, and/or pyrolytic carbon on the barrier layer. After depositing the wetting layer, a fiber preform comprising the silicon carbide fibers is infiltrated with a slurry. After slurry infiltration, the fiber preform is infiltrated with a melt comprising silicon, and then the melt is cooled, thereby forming a ceramic matrix composite.
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99.发明申请公开(公告)号：US20220055955A1
公开(公告)日：2022-02-24
申请号：US16997094
申请日：2020-08-19
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Richard Kidd , Sungbo Shim , Kelly Kranjc , Robert Shinavski
IPC: C04B35/80 , C04B35/628 , C04B35/657 , C04B35/65
Abstract: A method of making a ceramic matrix composite that exhibits moisture and environmental resistance has been developed. The method includes depositing a diffusion barrier layer comprising boron nitride on silicon carbide fibers and depositing a moisture-tolerant layer comprising silicon-doped boron nitride on the diffusion barrier layer, where a thickness of the moisture-tolerant layer is from about 3 to about 300 times a thickness of the diffusion barrier layer. Thus, a compliant multilayer including the moisture-tolerant layer and the diffusion barrier layer is formed. A wetting layer comprising silicon carbide, boron carbide, and/or pyrolytic carbon is deposited on the compliant multilayer layer. After depositing the wetting layer, a fiber preform comprising the silicon carbide fibers is infiltrated with a slurry. After slurry infiltration, the fiber preform is infiltrated with a melt comprising silicon and then the melt is cooled, thereby forming a ceramic matrix composite.
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公开(公告)号：US11255210B1
公开(公告)日：2022-02-22
申请号：US17082740
申请日：2020-10-28
Inventor： Ted J. Freeman , Jeremy Roehm
Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment that is supported by the carrier relative to a high temperature zone. The blade track segment provides a heat shield for use in high temperature applications protecting the carrier and other components.
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