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公开(公告)号：US11813706B2
公开(公告)日：2023-11-14
申请号：US17401947
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
IPC: B23P15/00
CPC classification number: B23P15/00 , B23P2700/06 , F05D2220/30 , F05D2230/90 , F05D2260/20
Abstract: A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate. An outer coating is applied over the substrate. A characteristic of the outer coating is determined. Instructions for forming a cooling aperture are revised based on the characteristic of the outer coating to provide revised instructions. The cooling aperture is formed in the outer coating and the substrate based on the revised instructions.
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Patent Agency Ranking
公开(公告)号：US20230052181A1
公开(公告)日：2023-02-16
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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公开(公告)号：US11428124B2
公开(公告)日：2022-08-30
申请号：US16197580
申请日：2018-11-21
Applicant: Raytheon Technologies Corporation
Inventor： Pedro Rivero , Brian Craig , Aaron T. Goldman
Abstract: A flange includes a flange body annularly disposed about a longitudinal axis. The flange body includes a first radial side and a second radial side radially opposite the first radial side. The flange body defines a first fastener hole and a circumferentially adjacent second fastener hole formed through the flange body. A first shielding zone has at least a portion of the first shielding zone located between the first and second fastener holes. A first shielding feature is disposed in the first shielding zone.
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公开(公告)号：US20230212951A1
公开(公告)日：2023-07-06
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
CPC classification number: F01D25/12 , F01D5/186 , F01D9/02 , F05D2220/32 , F05D2240/12 , F05D2240/30 , 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：US20230049566A1
公开(公告)日：2023-02-16
申请号：US17401947
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. An outer coating is applied over the substrate. A characteristic of the outer coating is determined. Instructions for forming a cooling aperture are revised based on the characteristic of the outer coating to provide revised instructions. The cooling aperture is formed in the outer coating and the substrate based on the revised instructions.
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公开(公告)号：US20230047576A1
公开(公告)日：2023-02-16
申请号：US17401899
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 this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.
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