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11.发明公开公开(公告)号：US20240165751A1
公开(公告)日：2024-05-23
申请号：US17993764
申请日：2022-11-23
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Brian Richard Craig , Brian T. Hazel , Luke Henry Rettberg , Xuan Liu , Michael J. Minor , Christopher J. Bischof , Stewart S. Fowler , Steven Ivory
CPC classification number: B23P6/005 , F01D5/005 , F05D2230/40 , F05D2230/80 , F05D2240/303
Abstract: A method can comprise forming a component comprising a first mating surface; coupling the component to an airfoil having a second mating surface and a Field Assisted Sintering Technology (“FAST”) system; heating, via the FAST system, the airfoil and the component; and applying, via the FAST system, a mechanical pressure between the first mating surface and the second mating surface to join the airfoil to the component and form a blade, the component at least partially defining a leading edge of the blade in response to joining the airfoil to the component
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公开(公告)号：US11913358B2
公开(公告)日：2024-02-27
申请号：US18120843
申请日：2023-03-13
Applicant: Raytheon Technologies Corporation
Inventor： Brian Craig , James M. Koonankeil , Brian T. Hazel , Paul E. Denney , Dominic J. Mongillo
IPC: B23K26/386 , F01D5/18 , F01D9/04 , B23K26/382 , C23C4/01 , C23C14/02 , C23C14/16 , C23C16/02 , C23C16/06 , F01D25/12 , F01D9/02
CPC classification number: F01D9/041 , B23K26/386 , B23K26/389 , C23C4/01 , C23C14/024 , C23C14/028 , C23C14/16 , C23C16/0263 , C23C16/0281 , C23C16/06 , F01D5/186 , F01D9/02 , F01D25/12 , B23P2700/00 , F05D2220/32 , F05D2230/10 , F05D2230/31 , F05D2240/12 , F05D2240/30 , F05D2260/20 , F05D2260/202
Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.
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公开(公告)号：US20230313993A1
公开(公告)日：2023-10-05
申请号：US17714064
申请日：2022-04-05
Applicant: Raytheon Technologies Corporation
Inventor： Tianli Zhu , Richard Wesley Jackson, III , John A. Sharon , James T. Beals , Brian T. Hazel
CPC classification number: F01D5/288 , F23R3/007 , F05D2230/31 , F05D2260/231 , F05D2300/143 , F05D2300/21 , F05D2300/504 , F05D2300/608 , F05D2300/611 , F23R2900/00018
Abstract: A gas turbine engine component having a substrate; a thermal barrier coating on the substrate having a porous microstructure; and a reflective layer conforming to the porous microstructure of the thermal barrier coating, wherein the reflective layer comprises a conforming nanolaminate defined by alternating layers of platinum group metal materials selected from the group consisting of platinum group metal-based alloys, platinum group metal intermetallic compounds, mixtures of platinum group metal with metal oxides and combinations thereof. A capping layer can be added over the reflective layer. A supporting layer can be added between the reflective layer and the thermal barrier coating. A process is also disclosed.
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公开(公告)号：US11732590B2
公开(公告)日：2023-08-22
申请号：US17401927
申请日：2021-08-13
Applicant: Raytheon Technologies Corporation
Inventor： Brian Craig , James M. Koonankeil , Brian T. Hazel , Paul E. Denney , Dominic J. Mongillo
CPC classification number: F01D5/186 , F01D25/12 , F05D2220/32 , F05D2260/202
Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.
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公开(公告)号：US20220297345A1
公开(公告)日：2022-09-22
申请号：US17401721
申请日：2021-08-13
Applicant: Raytheon Technologies Corporation
Inventor： Xuan Liu , James T. Beals , Xia Tang , Justin R. Hawkes , Olivier H. Sudre , William F. Werkheiser , Brian T. Hazel , Richard Wesley Jackson
Abstract: A method of forming a coating includes providing a mold that has a flexible wall that defines a mold cavity, inserting a component that is to be coated into the mold cavity, the component having a component surface roughness and there being a coating gap defined between the component and the flexible wall of the mold cavity, introducing a molding slurry into the mold cavity, the molding slurry filling the coating gap and contacting the component so as to overcoat the component surface roughness, solidifying the molding slurry to form a green coating on the component, and consolidating the green coating to form a final coating on the component, the final coating having a coating surface roughness that is less than the component surface roughness.
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Patent Agency Ranking
公开(公告)号：US20210324506A1
公开(公告)日：2021-10-21
申请号：US17359855
申请日：2021-06-28
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Christopher W. Strock, III , Michael J. Maloney , David A. Litton , Benjamin Joseph Zimmerman , Brian T. Hazel
Abstract: A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a substrate, a thermal barrier coating deposited on at least a portion of the substrate, and an outer layer deposited on at least a portion of the thermal barrier coating. The outer layer can include a material that is reactive with an environmental contaminant that comes into contact with the outer layer to alter a microstructure of the outer layer.
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公开(公告)号：US20210040854A1
公开(公告)日：2021-02-11
申请号：US17077459
申请日：2020-10-22
Applicant: Raytheon Technologies Corporation
Inventor： Brian T. Hazel , Kevin W. Schlichting , Michael J. Maloney
Abstract: Disclosed herein is a method comprising mixing a carrier liquid with particles and/or with a particle precursor to form a suspension or solution respectively; where the particles comprise a metal oxide; and where the particle precursor comprises a metal salt; injecting the suspension or solution through a plasma flame; and depositing the particles and/or the particle precursor onto a substrate to form an first abradable coating; where the first abradable coating comprises a plurality of cracks or voids that are substantially perpendicular to the substrate surface, where the substrate is a hub surface of a gas turbine engine or where the substrate is a cantilever stator.
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公开(公告)号：US20240247594A1
公开(公告)日：2024-07-25
申请号：US18157483
申请日：2023-01-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Robert A. White, III , Brian T. Hazel , Zhongfen Ding
IPC: F01D11/00
CPC classification number: F01D11/00 , F05D2220/32 , F05D2300/2261 , F05D2300/6033 , F05D2300/611
Abstract: A seal system a ceramic component having a surface region defining a first surface roughness, a metallic component situated adjacent the surface region, and a coating system disposed on the surface region. The coating system includes a silicon-containing layer on the surface region and a barrier layer on the silicon-containing layer. The silicon-containing layer has a surface in contact with the barrier layer. 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 limits interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer has a coefficient of thermal expansion that is within about 60% of a coefficient of thermal expansion of the ceramic component. A gas turbine engine and a method are also disclosed.
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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：US11913119B2
公开(公告)日：2024-02-27
申请号：US17401966
申请日：2021-08-13
Applicant: Raytheon Technologies Corporation
Inventor： Brian Craig , James M. Koonankeil , Brian T. Hazel , Paul E. Denney , Dominic J. Mongillo
Abstract: A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate and a locating feature at an exterior surface of the substrate. An outer coating is applied over the substrate. The outer coating covers the locating feature. At least a portion of the preform component and the outer coating are scanned with an imaging system to provide scan data indicative of a location of the locating feature. A cooling aperture is formed in the substrate and the outer coating based on the scan data.
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