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公开(公告)号：US11674448B2
公开(公告)日：2023-06-13
申请号：US17377591
申请日：2021-07-16
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Brian T. Hazel , Robert A. White, III , Zhongfen Ding
CPC classification number: F02C7/28 , F01D11/001 , F01D11/005 , F01D11/08 , F02C3/04 , F16J15/16 , F05D2220/32 , F05D2240/35 , F05D2240/55
Abstract: A seal system includes a ceramic component, a metallic component, a silicon-containing layer, and a barrier layer. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The silicon-containing layer is on the first surface region of the ceramic component and has a contact surface that defines a second surface roughness which is less than the first surface roughness. The barrier layer is on the metallic component and in contact with the silicon-containing layer and serves to limit interaction between silicon of the silicon-containing layer and the metallic component. The barrier layer includes at least one of alumina or MCrAlY.
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公开(公告)号：US20230019497A1
公开(公告)日：2023-01-19
申请号：US17377591
申请日：2021-07-16
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Brian T. Hazel , Robert A. White, III , Zhongfen (Vivian) Ding
Abstract: A seal system includes a ceramic component, a metallic component, a silicon-containing layer, and a barrier layer. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The silicon-containing layer is on the first surface region of the ceramic component and has a contact surface that defines a second surface roughness which is less than the first surface roughness. The barrier layer is on the metallic component and in contact with the silicon-containing layer and serves to limit interaction between silicon of the silicon-containing layer and the metallic component. The barrier layer includes at least one of alumina or MCrAlY.
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公开(公告)号：US20220356810A1
公开(公告)日：2022-11-10
申请号：US17307139
申请日：2021-05-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Howard J. Liles
Abstract: A seal assembly includes first, second, and third gas turbine engine components, such as vane assemblies, that are successively arranged around an axis. Each component has first and second mate faces such that the first mate face of the first component and the second mate face of the second component define a first mate face gap, and the first mate face of the second component and the second mate face of the third component to define a second mate face gap. A seal arc segment has first and second seal portions and a connector portion that joins the seal portions. The first seal portion bridges the first mate face gap to seal the first mate face gap, the second seal portion bridges the second mate face gap to seal the second mate face gap, and the connector portion spans circumferentially across the second component.
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公开(公告)号：US20220341334A1
公开(公告)日：2022-10-27
申请号：US17236014
申请日：2021-04-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace
Abstract: A vane assembly includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar leg that extends through the hollow airfoil section. The spar leg has a through-passage and an end portion that protrudes from the second fairing platform. A support is secured with the end portion of the spar leg. The support has a platform that includes first and second sides, an opening that extends between the first and second sides, and a nozzle tube that extends from the second side. The first side is adjacent the second fairing platform. The end portion of the spar leg is disposed in the opening so as to fluidly connect the through-passage with the nozzle tube.
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公开(公告)号：US20240229239A9
公开(公告)日：2024-07-11
申请号：US17970990
申请日：2022-10-21
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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Patent Agency Ranking
公开(公告)号：US20240044258A1
公开(公告)日：2024-02-08
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 , F05D2240/12 , F05D2230/60
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：US11781432B2
公开(公告)日：2023-10-10
申请号：US17385271
申请日：2021-07-26
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Kathryn S. Read , Raymond Surace
CPC classification number: F01D5/081 , F01D5/282 , F01D5/284 , F05D2240/81 , F05D2260/201 , F05D2260/221 , F05D2300/6033 , F05D2300/6034
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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公开(公告)号：US11674404B2
公开(公告)日：2023-06-13
申请号：US17307139
申请日：2021-05-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Howard J. Liles
CPC classification number: F01D11/08 , F01D9/04 , F01D11/001 , F01D11/005 , F01D25/12 , F02C7/28 , F05D2220/323 , F05D2240/11 , F05D2240/56 , F05D2260/201 , F05D2300/6033
Abstract: A seal assembly includes first, second, and third gas turbine engine components, such as vane assemblies, that are successively arranged around an axis. Each component has first and second mate faces such that the first mate face of the first component and the second mate face of the second component define a first mate face gap, and the first mate face of the second component and the second mate face of the third component to define a second mate face gap. A seal arc segment has first and second seal portions and a connector portion that joins the seal portions. The first seal portion bridges the first mate face gap to seal the first mate face gap, the second seal portion bridges the second mate face gap to seal the second mate face gap, and the connector portion spans circumferentially across the second component.
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公开(公告)号：US11603770B2
公开(公告)日：2023-03-14
申请号：US17236014
申请日：2021-04-21
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace
Abstract: A vane assembly includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar leg that extends through the hollow airfoil section. The spar leg has a through-passage and an end portion that protrudes from the second fairing platform. A support is secured with the end portion of the spar leg. The support has a platform that includes first and second sides, an opening that extends between the first and second sides, and a nozzle tube that extends from the second side. The first side is adjacent the second fairing platform. The end portion of the spar leg is disposed in the opening so as to fluidly connect the through-passage with the nozzle tube.
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公开(公告)号：US20230015977A1
公开(公告)日：2023-01-19
申请号：US17378005
申请日：2021-07-16
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Brian T. Hazel , Raymond Surace , Robert A. White, III , Zhongfen Ding
Abstract: A seal system includes a ceramic component, a metallic component, a coating system. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The coating system includes a silicon-containing layer on the surface region of the ceramic component and barrier layer on the silicon-containing layer. The silicon containing layer has a surface in contact with the barrier layer and the barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer serves to limit interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer includes at least one of mullite, zircon, or hafnon.
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