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.

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

IPC: F01D5/18 ,  F01D25/12

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.

公开(公告)号：US11603769B2

公开(公告)日：2023-03-14

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

IPC: B23K26/386 ,  C23C4/01 ,  F01D9/04 ,  F01D25/12 ,  C23C14/02 ,  C23C14/16 ,  C23C16/02 ,  C23C16/06 ,  B23K26/382

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.

公开(公告)号：US20230052285A1

公开(公告)日：2023-02-16

申请号：US17401886

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: B23K26/382 ,  B23K26/00 ,  B23H9/14 ,  B24C1/04

Abstract: A manufacturing method is provided. During this method, a preform component for a turbine engine is provided. This preform component includes a substrate and an outer coating on the substrate. A cooling aperture is formed in the preform component. The cooling aperture includes a diffuser section and a meter section. The diffuser section extends through the outer coating and into the substrate. The meter section extends within the substrate. The forming of the cooling aperture includes: forming the diffuser section using a first machining process; and forming the meter section using a second machining process that is different than the first machining process.

公开(公告)号：US20230050204A1

公开(公告)日：2023-02-16

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

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12

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.

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.

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.

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

IPC: C23C28/00 ,  G01N22/00

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.

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

IPC: F23R3/60 ,  F01D25/24 ,  F01D9/02

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.

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

IPC: C23C28/00 ,  G01N22/00

CPC classification number: C23C28/34 ,  G01N22/00

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.