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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：US11434768B2
公开(公告)日：2022-09-06
申请号：US17322211
申请日：2021-05-17
Applicant: Raytheon Technologies Corporation
Inventor： Christopher J. Peters , Emma J. Place , Jeffrey J. DeGray , Dominic J. Mongillo , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.
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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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Patent Agency Ranking
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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公开(公告)号：US20230051153A1
公开(公告)日：2023-02-16
申请号：US17401906
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 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：US11542831B1
公开(公告)日：2023-01-03
申请号：US17401931
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: F01D25/12
Abstract: A manufacturing method is provided during which a preform component for a turbine engine is provided. A cooling aperture is formed in the preform component. The cooling aperture includes a centerline, an inlet and an outlet. The cooling aperture extends longitudinally along the centerline through a wall of the preform component from the inlet to the outlet. The forming of the cooling aperture includes forming a first portion of the cooling aperture using a machining tool implement with a first toolpath that is angularly offset from the centerline by a first angle between thirty-five degrees and ninety degrees.
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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：US11913353B2
公开(公告)日：2024-02-27
申请号：US17881803
申请日：2022-08-05
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Emma J. Place , Dominic J. Mongillo , Jeremy B. Fredette
CPC classification number: F01D5/186 , F01D5/141 , F05D2220/323 , F05D2240/30 , F05D2260/202
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.
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