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61.发明申请公开(公告)号：US20210102470A1
公开(公告)日：2021-04-08
申请号：US16593535
申请日：2019-10-04
Inventor： Daniel K. Vetters , Jeffrey M. Crutchfield
Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gases from passing over turbine blades included in the gas turbine engine.
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62.发明申请公开(公告)号：US20210101841A1
公开(公告)日：2021-04-08
申请号：US16596054
申请日：2019-10-08
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Andrew J. Ritchey
IPC: C04B35/628 , C04B40/00 , C04B35/80 , C23C16/458 , C23C16/04
Abstract: A method of infiltrating a fiber preform comprises positioning an assembly in a process chamber, where the assembly includes a tool comprising through-holes, a fiber preform constrained within the tool, and a sacrificial preform disposed between the fiber preform and the tool. The sacrificial preform is gas permeable. The process chamber is heated, and gaseous reactants are delivered into the process chamber during the heating. The gaseous reactants penetrate the through-holes of the tool and infiltrate the sacrificial preform and the fiber preform. Deposition of reaction products occurs on exposed surfaces of the fiber preform and the sacrificial preform, and a coating is formed thereon. In addition, the sacrificial preform accumulates excess coating material formed from increased reactions at short diffusion depths. Accordingly, the coating formed on the fiber preform exhibits a thickness variation of about 10% or less throughout a volume of the fiber preform.
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公开(公告)号：US10941942B2
公开(公告)日：2021-03-09
申请号：US14971535
申请日：2015-12-16
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Ted J. Freeman , Wayne S. Steffier
Abstract: A combustor of a gas turbine engine and a turbine shroud for a turbine of a gas turbine engine are disclosed. The combustor is configured to ignite a mixture of compressed air and fuel in a combustion chamber included therein. The turbine shroud is configured to direct products of the combustion reaction toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate.
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64.发明授权公开(公告)号：US10759711B2
公开(公告)日：2020-09-01
申请号：US15995537
申请日：2018-06-01
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Stephen Harris
IPC: C04B35/571 , C04B35/80 , C04B35/565 , C04B35/58 , C04B35/10 , C04B35/18 , C04B35/563 , F01D5/28 , C04B35/573 , C04B41/00 , C04B41/87 , C04B41/50 , F23R3/00
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.
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公开(公告)号：US10717116B2
公开(公告)日：2020-07-21
申请号：US15967005
申请日：2018-04-30
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Christopher Barrett
IPC: C04B35/565 , C04B35/573 , B08B9/04 , C04B35/80 , C04B35/628 , C04B35/00
Abstract: A method of slurry infiltration and cleaning to fabricate a ceramic matrix composite (CMC) component with an internal cavity or bore comprises inserting a number of rods into a hollow portion of a porous fiber preform, thereby forming a rod arrangement substantially filling the hollow portion. Each of the rods has a low-friction surface comprising a coefficient of static friction of about 0.1 or less. The porous fiber preform is exposed to a slurry comprising particulate solids in a liquid carrier, and the slurry infiltrates the porous fiber preform. Some fraction of the particulate solids is deposited within interstices of the porous fiber preform to form an impregnated fiber preform, and another fraction of the particulate solids is deposited within the hollow portion as excess slurry. After slurry infiltration, the rods are withdrawn from the hollow portion, and at least some of the excess slurry is removed with the rods.
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Patent Agency Ranking
公开(公告)号：US10683764B2
公开(公告)日：2020-06-16
申请号：US15896557
申请日：2018-02-14
Inventor： Stephen I. Harris , Robert J. Shinavski , Richard W. Kidd , Sungbo Shim , Kang N. Lee
IPC: F01D5/28 , C04B35/80 , F01D11/12 , C04B35/628 , C04B41/89 , C04B41/00 , C04B41/52 , C04B35/573 , C04B41/50
Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.
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公开(公告)号：US10584605B2
公开(公告)日：2020-03-10
申请号：US15672991
申请日：2017-08-09
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce plc
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Joseph P. Lamusga , Brian J. Shoemaker , Steven Hillier
Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
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公开(公告)号：US20200063571A1
公开(公告)日：2020-02-27
申请号：US16113502
申请日：2018-08-27
Applicant: Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc.
Inventor： Ted J. Freeman , Aaron D. Sippel , Robert J. Shinavski
Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes an airfoil and a tip to discourage air leakage over the tip of the turbine blade. The turbine blade is designed considering weight and strength to include a lightening hole.
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公开(公告)号：US20190389782A1
公开(公告)日：2019-12-26
申请号：US16539644
申请日：2019-08-13
Inventor： Sungbo Shim , Robert Wesley Thibault , Robert Shinavski , Kang N. Lee
IPC: C04B41/89 , C04B41/52 , C04B41/50 , C04B41/45 , C04B41/00 , C04B35/80 , C04B35/626 , C04B41/85 , C04B41/81 , C04B35/573
Abstract: The disclosure describes techniques for forming a surface layer of an article including a CMC using a cast. In some examples, the surface layer includes three-dimensional surface features, which may increase adhesion between the CMC and a coating on the CMC. In some examples, the surface layer may include excess material, with or without three-dimensional surface features, which is on the CMC. The excess material may be machined to remove some of the excess material and facilitate conforming the article to dimensional tolerances, e.g., for fitting the article to another component. The excess material may reduce a likelihood that the CMC (e.g., reinforcement material in the CMC) is damaged by the machining.
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公开(公告)号：US20190389777A1
公开(公告)日：2019-12-26
申请号：US16017457
申请日：2018-06-25
Inventor： Jun Shi , Sungbo Shim
IPC: C04B35/80 , C04B35/628 , C04B35/657 , F01D5/14 , F01D5/28
Abstract: A blade for a gas turbine engine, and methods of manufacture of such a blade having a continuous density gradient so that the portion of the blade nearest the rotator shaft is of a higher density than the portion of the blade furthest from the rotator shaft.
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