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公开(公告)号：US20220162945A1
公开(公告)日：2022-05-26
申请号：US17102575
申请日：2020-11-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Mark F. Zelesky
Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.
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公开(公告)号：US20240401485A1
公开(公告)日：2024-12-05
申请号：US18328217
申请日：2023-06-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Russell Kim , Raymond Surace , James T. Roach , Jonas Banhos
Abstract: An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side, a flange that extends from the non-gaspath side, and a gaspath side from which the airfoil section extends. The flange is comprised of a sandwich composite that includes first and second ceramic matrix composite (CMC) skins that each have at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins.
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公开(公告)号：US12006842B1
公开(公告)日：2024-06-11
申请号：US18328177
申请日：2023-06-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Russell Kim , Raymond Surace , James T. Roach , Jonas Banhos
CPC classification number: F01D5/282 , F01D5/147 , F01D5/284 , F05D2240/80 , F05D2250/283 , F05D2300/6033 , F05D2300/612
Abstract: An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side and a gaspath side from which the airfoil section extends. The platform is comprised of a sandwich composite that has first and second ceramic matrix composite (CMC) skins that each include at least one 2-D ceramic fiber ply. The first and second CMC skins are disposed, respectively, on the gaspath side and the non-gaspath side, and there is a cellular core disposed radially between the first and second CMC skins.
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公开(公告)号：US12006836B2
公开(公告)日：2024-06-11
申请号：US17856042
申请日：2022-07-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Dominic J. Mongillo , Emma J. Place , Christopher J. Peters , Jeffrey J. DeGray , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
IPC: F01D5/18
CPC classification number: F01D5/18 , F05D2220/32 , F05D2230/60 , F05D2260/20
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.
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公开(公告)号：US20240175372A1
公开(公告)日：2024-05-30
申请号：US18070978
申请日：2022-11-29
Applicant: Raytheon Technologies Corporation
Inventor： Robert A. White, III , Raymond Surace , Howard J. Liles , Bryan P. Dube
CPC classification number: F01D25/005 , F01D9/041 , F05D2220/323 , F05D2230/10 , F05D2240/12 , F05D2300/6033
Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.
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Patent Agency Ranking
公开(公告)号：US11988104B1
公开(公告)日：2024-05-21
申请号：US18070978
申请日：2022-11-29
Applicant: Raytheon Technologies Corporation
Inventor： Robert A. White, III , Raymond Surace , Howard J. Liles , Bryan P. Dube
CPC classification number: F01D25/005 , F01D9/041 , F05D2220/323 , F05D2230/10 , F05D2240/12 , F05D2300/6033
Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.
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公开(公告)号：US20240109814A1
公开(公告)日：2024-04-04
申请号：US17957605
申请日：2022-09-30
Applicant: Raytheon Technologies Corporation
Inventor： Raymond Surace , Brendan Lenz
IPC: C04B35/622
CPC classification number: C04B35/62281 , C04B2235/5244 , C04B2235/614
Abstract: An assembly for use in releasing a preform from a tooling fixture comprises a solid body engageable with the fixture via a seal, a manifold formed in the solid body and in flow communication with the preform via a plurality of holes in the tooling fixture, and a fluid source in flow communication with the manifold and configured to supply fluid to the manifold. The fluid comprises at least one of a gas and a slurry.
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公开(公告)号：US11788419B1
公开(公告)日：2023-10-17
申请号：US17887870
申请日：2022-08-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jonas Banhos , Ravon Venters , Russell Kim , Raymond Surace , James T. Roach
CPC classification number: F01D5/187 , F01D5/282 , F01D5/284 , F05D2240/121 , F05D2240/303 , F05D2300/6033
Abstract: A ceramic matrix composite airfoil includes a high-pressure surface and a low-pressure surface connected at a leading edge and a trailing edge. The high-pressure surface and the low-pressure surface extend from a first end to a second end. A leading edge cooling passage includes an inlet portion, a midspan portion and an outlet portion. A cross-sectional flow area of the midspan portion is less than a cross-sectional flow area of either the inlet portion or the outlet portion.
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公开(公告)号：US11781486B2
公开(公告)日：2023-10-10
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
CPC classification number: F02C7/28 , F02C3/04 , F16J15/16 , C23C4/11 , C23C4/134 , C23C4/18 , F05D2220/32 , F05D2240/35 , F05D2300/611
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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公开(公告)号：US20230250725A1
公开(公告)日：2023-08-10
申请号：US17856042
申请日：2022-07-01
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Dominic J. Mongillo , Emma J. Place , Christopher J. Peters , Jeffrey J. DeGray , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
IPC: F01D5/18
CPC classification number: F01D5/18 , F05D2220/32 , F05D2230/60 , F05D2260/20
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.
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