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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：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：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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Patent Agency Ranking
公开(公告)号：US11898465B2
公开(公告)日：2024-02-13
申请号：US17401914
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: F01D5/28 , F01D5/00 , F01D5/18 , B23K26/382 , C23C4/073 , C23C4/11 , B23K101/00 , B23H9/10 , B23H9/14 , B23P9/00 , B23P15/02 , C23C4/06 , C23C4/12 , C23C4/16
CPC classification number: F01D5/288 , F01D5/005 , F01D5/186 , F01D5/284 , B23H9/10 , B23H9/14 , B23K26/389 , B23K2101/001 , B23P9/00 , B23P15/02 , B23P2700/06 , C23C4/06 , C23C4/073 , C23C4/11 , C23C4/12 , C23C4/16 , F05D2230/11 , F05D2230/90 , F05D2260/202 , F05D2300/2112
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 preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.
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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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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：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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公开(公告)号：US20230052105A1
公开(公告)日：2023-02-16
申请号：US17401914
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 is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.
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