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公开(公告)号：US20240246872A1
公开(公告)日：2024-07-25
申请号：US18157450
申请日：2023-01-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Robert A. White, III , Brian T. Hazel , Raymond Surace
CPC classification number: C04B41/87 , C04B41/5035 , C04B41/5042 , C04B41/5057 , C04B41/522
Abstract: A section of a gas turbine engine includes a ceramic component, a metallic component, a seal situated between the metallic component and the ceramic component at a sealing interface, a silicon-based coating disposed on the ceramic component at the sealing interface, and a non-reactive coating disposed on the metallic component at the sealing interface. The non-reactive coating provides thermochemical protection against interaction between the ceramic component, the silicon-based coating, and the metallic component. A method of providing a seal in a gas turbine engine is also disclosed.
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公开(公告)号：US20240139998A1
公开(公告)日：2024-05-02
申请号：US17977370
申请日：2022-10-31
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace
Abstract: A method includes providing a continuous mandrel body disposed along an axis. The mandrel body defines, in order along the axis from a first end thereof, a pilot lead-in section, a first article section, a tapered transition section, and a second article section. Beginning at the pilot lead-in section, a continuous fabric sleeve is progressively formed on the mandrel body to the first article section, to the tapered transition section, and then to the second article section to form a fabric-covered mandrel. The portions of the continuous fabric sleeve that are on the first article section and the second article section form, respectively, a first article preform and a second article preform. The fabric-covered mandrel is then divided to separate the article preforms, followed by densifying the article preforms with a ceramic matrix material to thereby form CMC articles.
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公开(公告)号：US11952917B2
公开(公告)日：2024-04-09
申请号：US17882041
申请日：2022-08-05
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： David J. Wasserman , Raymond Surace
CPC classification number: F01D9/042 , F01D25/005 , F05D2220/32 , F05D2230/60 , F05D2240/12
Abstract: A vane multiplet includes first and second ceramic matrix composite (CMC) singlet vanes that are arranged circumferentially adjacent each other. Each of the CMC singlet vanes includes an airfoil section and a platform at one end of the airfoil section. The platform defines forward and trailing platform edges and first and second circumferential side edges. A CMC overwrap conjoins the CMC singlet vanes. The CMC overwrap includes fiber plies that are fused to the platforms of the CMC singlet vanes.
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公开(公告)号：US11725522B2
公开(公告)日：2023-08-15
申请号：US17149944
申请日：2021-01-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jonas S. Banhos , Kathryn S. Read , Raymond Surace , Olivier H. Sudre
CPC classification number: F01D5/282 , F01D5/147 , F01D5/18 , F05D2200/11 , F05D2240/301 , F05D2240/304 , F05D2250/75 , F05D2300/6033 , F05D2300/6034
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.
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公开(公告)号：US20230235705A1
公开(公告)日：2023-07-27
申请号：US18153509
申请日：2023-01-12
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Brian T. Hazel , Raymond Surace , Robert A. White, III , Zhongfen Ding
Abstract: A seal system includes a ceramic component that has a non-core-gaspath surface region that defines a first surface roughness and a core gaspath surface region. A metallic component is situated adjacent the non-core-gaspath surface region. A coating system is disposed on the ceramic component. The coating system includes a silicon-containing layer on the non-core-gaspath surface region and a barrier layer that has a first section on the silicon-containing layer and a second section on the core-gaspath region and that is connected to the first section. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The first section is in contact with the metallic component and the second section serves as an environmental barrier on the core-gaspath region.
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Patent Agency Ranking
公开(公告)号：US20250003589A1
公开(公告)日：2025-01-02
申请号：US18343198
申请日：2023-06-28
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jonas Banhos , James T. Roach , Russell Kim , Raymond Surace
Abstract: A combustor includes a combustion chamber and a liner that bounds at least a portion of the combustion chamber. The liner includes a first side facing the combustion chamber and a second side facing away from the combustion chamber. The liner is formed of a lay-up of ceramic matrix composite (CMC) plies that have a first CMC ply on the first side, a second CMC ply on the second side, and intermediate CMC plies between the first and second CMC plies. At least one of the intermediate CMC plies has a pattern of voids that define cooling channels in the combustor panel. The cooling channels are bound on lateral channel sides by the at least one of the intermediate CMC plies.
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公开(公告)号：US12152505B2
公开(公告)日：2024-11-26
申请号：US17994490
申请日：2022-11-28
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Mark F. Zelesky
Abstract: Disclosed is a method of reducing play in a vane arc segment. The vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the radial flange, and a thermal insulation element is located adjacent the radial flange. The method includes performing a light scan of the radial flange to produce a digital three-dimensional model of the radial flange, and then machining the thermal insulation element in accordance with the digital three-dimensional model to provide a low-tolerance fit between the radial flange and the thermal insulation element that limits play between the airfoil piece and the thermal insulation element.
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公开(公告)号：US20240133034A1
公开(公告)日：2024-04-25
申请号：US17970990
申请日：2022-10-20
Applicant: Raytheon Technologies Corporation
Inventor： Alyson T. Burdette , Raymond Surace , Jon Erik Sobanski
IPC: C23C16/458 , C23C16/04
CPC classification number: C23C16/458 , C23C16/045
Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture and an inner tooling fixture. The outer tooling fixture comprises a first portion removably attached to a second portion, and a first pair of oppositely disposed windows defined by the first portion and the second portion. Each of the first portion and the second portion comprise a base with a recess. The inner tooling fixture comprises a body defined by at least one portion, the body configured to at least partially surround the fibrous preform, a plurality of holes extending through a thickness of the at least one portion, each hole of the plurality of holes having a length (L) and a diameter (D), and a first neck region engageable with a recess of the first portion or the second portion.
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公开(公告)号：US20230407755A1
公开(公告)日：2023-12-21
申请号：US17843434
申请日：2022-06-17
Applicant: Raytheon Technologies Corporation
Inventor： Raymond Surace , Robert A. White, III
IPC: F01D9/04
CPC classification number: F01D9/041 , F05D2240/12 , F05D2230/60 , F05D2300/6033 , F05D2300/175
Abstract: An assembly for a gas turbine engine includes a plurality of vanes having a radially outer platform with a flange that extends radially outward therefrom and a plurality of notches in the flange. A ring is located radially outward from the radially outer platform of the plurality of vanes. An axially extending projection extends through and corresponds with each of the plurality of notches on the flange.
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公开(公告)号：US20230026977A1
公开(公告)日：2023-01-26
申请号：US17385271
申请日：2021-07-26
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Kathryn S. Read , Raymond Surace
Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes at least one platform having a main body extending between a first mate face and a second mate face to establish a gas path surface. The main body has an internal passage extending circumferentially between a first opening along the first mate face and a second opening along the second mate face relative to an assembly axis. A perimeter of the first mate face establishes a first area, a perimeter of the second opening establishes a second area, and the second area is greater than the first area. An airfoil section extends radially from the at least one platform.
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