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公开(公告)号：US20230241699A1
公开(公告)日：2023-08-03
申请号：US18152482
申请日：2023-01-10
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Nicholas M. LoRicco , Xuan Liu
IPC: B23H7/24
CPC classification number: B23H7/24
Abstract: An electrode includes a metallic electrode body that has a surface region that is enriched in at least one of aluminum or chromium. The aluminum and/or chromium that is vaporized from the surface region suppresses vaporization loss of aluminum or chromium from the machined surface of the metallic workpiece during electric discharge machining.
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公开(公告)号：US11346230B1
公开(公告)日：2022-05-31
申请号：US16780368
申请日：2020-02-03
Applicant: Raytheon Technologies Corporation
Inventor： Alex J. Schneider , Parth Jariwala , Nicholas M. LoRicco , Ryan Lundgreen , David A. Niezelski , Jeffrey T. Morton
Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.
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公开(公告)号：US11506129B2
公开(公告)日：2022-11-22
申请号：US16858036
申请日：2020-04-24
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco
Abstract: A component for a gas turbine engine includes a mateface with a purge flow interface, the mateface comprises a pocket located in communication with a feather seal slot in a mateface. A vane for a gas turbine engine includes a platform that extends from the airfoil, the platform comprising a mateface with a feather seal slot and a pocket in communication with the feather seal slot, wherein the pocket is of a cross-sectional shape larger than the feather seal slot.
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公开(公告)号：US20220098988A1
公开(公告)日：2022-03-31
申请号：US17429097
申请日：2020-02-07
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Parth Jariwala , Alex J. Schneider , Bret M. Teller , Matthew S. Gleiner , Jeffrey T. Morton
Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
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公开(公告)号：US11661852B2
公开(公告)日：2023-05-30
申请号：US17429097
申请日：2020-02-07
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Parth Jariwala , Alex J. Schneider , Bret M. Teller , Matthew S. Gleiner , Jeffrey T. Morton
CPC classification number: F01D5/187 , F01D5/087 , F05D2240/304 , F05D2250/711 , F05D2250/712 , F05D2260/201
Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
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Patent Agency Ranking
公开(公告)号：US11248481B2
公开(公告)日：2022-02-15
申请号：US16850672
申请日：2020-04-16
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Efrain E. Vega , Rafael A. Perez
Abstract: Vane assemblies for turbine engines are described. The vane assemblies include a vane having an internal cavity and a vane platform and a vane rail defining, in part, an outer diameter supply cavity. A blade outer air seal support (BOAS support) is arranged adjacent the vane and engages with a portion of the vane, the blade outer air seal support having BOAS support rail, and a BOAS supported on the BOAS support and engaging with a portion of the vane. The BOAS support includes a first cooling flow aperture configured to enable a cooling flow to cool at least the BOAS and a second cooling flow aperture formed in the BOAS support rail. The vane rail includes a third cooling flow aperture to form a cooling flow path through the second cooling flow aperture and the third cooling flow aperture to fluidly connect to the outer diameter supply cavity.
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公开(公告)号：US11208898B1
公开(公告)日：2021-12-28
申请号：US16780368
申请日：2020-02-03
Applicant: Raytheon Technologies Corporation
Inventor： Alex J. Schneider , Parth Jariwala , Nicholas M. LoRicco , Ryan Lundgreen , David A. Niezelski , Jeffrey T. Morton
Abstract: A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.
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8.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：US20210332761A1
公开(公告)日：2021-10-28
申请号：US16858036
申请日：2020-04-24
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco
Abstract: A component for a gas turbine engine includes a mateface with a purge flow interface, the mateface comprises a pocket located in communication with a feather seal slot in a mateface. A vane for a gas turbine engine includes a platform that extends from the airfoil, the platform comprising a mateface with a feather seal slot and a pocket in communication with the feather seal slot, wherein the pocket is of a cross-sectional shape larger than the feather seal slot.
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公开(公告)号：US20210324753A1
公开(公告)日：2021-10-21
申请号：US16850672
申请日：2020-04-16
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas M. LoRicco , Efrain E. Vega , Rafael A. Perez
Abstract: Vane assemblies for turbine engines are described. The vane assemblies include a vane having an internal cavity and a vane platform and a vane rail defining, in part, an outer diameter supply cavity. A blade outer air seal support (BOAS support) is arranged adjacent the vane and engages with a portion of the vane, the blade outer air seal support having BOAS support rail, and a BOAS supported on the BOAS support and engaging with a portion of the vane. The BOAS support includes a first cooling flow aperture configured to enable a cooling flow to cool at least the BOAS and a second cooling flow aperture formed in the BOAS support rail. The vane rail includes a third cooling flow aperture to form a cooling flow path through the second cooling flow aperture and the third cooling flow aperture to fluidly connect to the outer diameter supply cavity.
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